Abstract

A water jet strengthening and polishing integrated system for blades of a blisk includes a vibration polishing unit and a water jet strengthening unit. The vibration polishing unit includes a vibration polishing bath, the vibration polishing bath is internally provided with a clamp for clamping the blisk, and vibration motors for driving the vibration polishing bath to vibrate are installed on the vibration polishing bath. Top ends of support springs are fixedly connected with the vibration polishing bath, and bottom ends of the support springs are fixedly connected with a workbench. The water jet strengthening unit includes a water jet strengthening device for carrying out water jet strengthening on the blades of the blisk and a driving mechanism for clamping the water jet strengthening device and capable of driving the water jet strengthening device to move in any direction in space.

IPC Classes  ?

• B24B 1/04 - Processes of grinding or polishingUse of auxiliary equipment in connection with such processes subjecting the grinding or polishing tools, the abrading or polishing medium or work to vibration, e.g. grinding with ultrasonic frequency
• B24B 19/14 - Single purpose machines or devices for particular grinding operations not covered by any other main group for grinding turbine blades, propeller blades or the like
• B24B 31/00 - Machines or devices designed for polishing or abrading surfaces on work by means of tumbling apparatus or other apparatus in which the work or the abrasive material is looseAccessories therefor
• B24B 31/06 - Machines or devices designed for polishing or abrading surfaces on work by means of tumbling apparatus or other apparatus in which the work or the abrasive material is looseAccessories therefor involving oscillating or vibrating containers
• B24B 31/12 - AccessoriesProtective equipment or safety devicesInstallations for exhaustion of dust or for sound absorption specially adapted for machines covered by group
• B24C 3/22 - Apparatus using nozzles
• B24C 3/28 - Apparatus using nozzles
• B24C 5/00 - Devices or accessories for generating abrasive blasts

Abstract

A method for processing a part using a forming device by laser melting, by: establishing a function, performing first-order and second-order differentiation on the function to obtain a first-order and a second-order derivative, solving the equation that the first-order derivative equals to zero, substituting the roots into the second-order derivative to obtain the roots of the first-order derivative, among which the root with a smallest absolute value is defined as a first value; performing third-order differentiation on the obtained function, solving the equation that the second-order derivative equals to zero to obtain the roots which is defined as second values; subtracting the first value from the second values, and obtaining the second value corresponding to a value that is less than zero and has a smallest absolute value among obtained results, that is a value of the defocus amount to achieve the optimal self-healing effect.

IPC Classes  ?

• B22F 10/366 - Scanning parameters, e.g. hatch distance or scanning strategy
• B22F 10/28 - Powder bed fusion, e.g. selective laser melting [SLM] or electron beam melting [EBM]
• B22F 10/31 - Calibration of process steps or apparatus settings, e.g. before or during manufacturing
• B22F 10/85 - Data acquisition or data processing for controlling or regulating additive manufacturing processes
• B33Y 10/00 - Processes of additive manufacturing
• B33Y 50/02 - Data acquisition or data processing for additive manufacturing for controlling or regulating additive manufacturing processes

Abstract

A fault diagnosis method for a gearbox, comprising: acquiring a preset parameter signal of a gearbox (S101), wherein the preset parameter signal comprises at least one of a signal of a rotational speed difference between an input shaft and an output shaft of the gearbox, and a vibration signal and an acoustic signal respectively corresponding to the input shaft, the output shaft, and a box body of the gearbox; acquiring a target time domain signal corresponding to the preset parameter signal (S102), wherein the target time domain signal comprises a parameter time domain residual signal and/or a parameter time domain difference signal; performing calculation to obtain a target signal kurtosis value corresponding to the target time domain signal (S103); determining whether the target signal kurtosis value satisfies a first fault determination condition (S104); and if yes, determining that a fault occurs in the gearbox (S104a). Further disclosed are a fault diagnosis system for a gearbox, an electronic device, and a computer readable storage medium.

IPC Classes  ?

• G01M 13/028 - Acoustic or vibration analysis
• G01M 13/021 - Gearings

Abstract

A method for repairing an ultra-thin structure by additive manufacturing by removing a damaged region of an ultra-thin structure by machining; acquiring a three-dimensional model of a region to be repaired; processing the three-dimensional model; constructing a powder carrying device on the periphery of the bottom of the region to be repaired, and allowing powder in the powder carrying device to be filled until flush with or tangent to the surface of the bottom of the region; melting, sintering or curing the powder around the outer contour of the ultra-thin structure by a high-energy beam or an auxiliary heating device, and combining the powder with the outer contour of the ultra-thin structure to form an outer contour thickened structure so as to form a flexible fixture; and repairing the region to be repaired by additive manufacturing technology according to a planned path obtained from the model processing.

IPC Classes  ?

• B22F 7/06 - Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting of composite workpieces or articles from parts, e.g. to form tipped tools
• B22F 10/28 - Powder bed fusion, e.g. selective laser melting [SLM] or electron beam melting [EBM]
• B22F 10/64 - Treatment of workpieces or articles after build-up by thermal means
• B22F 10/66 - Treatment of workpieces or articles after build-up by mechanical means
• B22F 10/85 - Data acquisition or data processing for controlling or regulating additive manufacturing processes
• B33Y 10/00 - Processes of additive manufacturing
• B33Y 40/20 - Post-treatment, e.g. curing, coating or polishing
• B33Y 50/02 - Data acquisition or data processing for additive manufacturing for controlling or regulating additive manufacturing processes

Abstract

Disclosed in the present invention are a flow dividing ring and an aero engine containing same, and an aircraft. The flow dividing ring is internally provided with an annular cavity, and the flow dividing ring is connected to an air intake pipe, which supplies gas into the annular cavity. The flow dividing ring further comprises a flow guide member, the flow guide member is arranged in the annular cavity, an end of the flow guide member in a flow guide direction of gas is arranged towards a circumferential direction of the annular cavity, and the other end of the flow guide member in the flow guide direction of the gas corresponds to a communication position between the air intake pipe and the annular cavity. By means of the present invention, the circulating flow rate of the gas, especially high-temperature gas in the annular cavity of the flow dividing ring that is supplied via the air intake pipe, is enhanced by means of the flow guide member, so that the high-temperature gas is distributed at each position of the annular cavity, and the high-temperature gas then heats an inner wall of the annular cavity; and the heating efficiency of the flow dividing ring is improved, and the efficiency of the flow dividing ring in heating and removing ice when the flow dividing ring encounters cold air is improved, thereby ensuring the flight safety of the aircraft.

IPC Classes  ?

• F02C 7/047 - Heating to prevent icing

Abstract

An inlet cone. The inlet cone comprises a body (2) and a nose cone portion (1), wherein the body (2) comprises an outer wall (21), and the nose cone portion (1) is connected to an end of the outer wall (21); an outer surface of the nose cone portion (1) has a first contour line (3), an outer surface of the outer wall (21) has a second contour line (4), and the second contour line (4) is bent and contracted towards the axis of the body (2) in a direction away from the first contour line (3); and cold air flows towards the rear outer wall (21) along the outer surface of the nose cone portion (1). Since the outer surface of the outer wall (21) is bent and contracted towards the axis of the body (2) in the direction away from the first contour line (3), an air stagnation zone is formed between an extension line of the first contour line (3) and the second contour line (4), and less cold air flows in the air stagnation zone, that is, the heat taken away by the cold air from a surface of the outer wall (21) is correspondingly reduced, such that the outer wall (21) of the inlet cone is not prone to icing up, and the engine efficiency is improved.

IPC Classes  ?

• F02C 7/04 - Air intakes for gas-turbine plants or jet-propulsion plants
• B64C 11/14 - Spinners

Abstract

A method includes simplifying flowing of airflow at root of a rotor blade into flowing of free jet, and determining an airflow expansion angle according to Mach number of incoming flow at root of a stator vane; calculating a radial height difference between a first end point on a leading edge of a stator platform and a trailing edge of an adjacent rotor platform by using an axial distance thereof, the angle and a deviation coefficient; determining position of the first end point with radial height difference; determining intersection point of the leading edge and the stator platform as position of a second end point on the leading edge; and determining a profile line between the points by bridging spline curves, so that the tail end thereof is tangent to the intersection line, and the starting end thereof is kept on same plane as side wall of the leading edge.

IPC Classes  ?

• F04D 29/32 - Rotors specially adapted for elastic fluids for axial-flow pumps

Abstract

Disclosed in the present invention are a turbine guide vane and a turbine containing same, and an aeroengine. The turbine guide vane comprises a guide vane body made of CMC material. The turbine guide vane further comprises a cover plate, an elastic bearing plate and a force-bearing component, wherein the elastic bearing plate comprises an upper support plate and a lower support plate, an elastic member is provided between the upper support plate and the lower support plate, and two ends of the guide vane body in a lengthwise direction thereof are respectively connected to the cover plate and the upper support plate; the force-bearing component is arranged in an inner cavity of the guide vane body, at least part of an outer surface of the force-bearing component abuts against a wall of the inner cavity of the guide vane body, an upper-end connecting portion of the force-bearing component is connected to the cover plate, and a lower-end connecting portion of the force-bearing component is connected to the lower support plate and causes the elastic member to be in a compressed state. By means of the turbine guide vane of the present invention, the problem of relatively large stress being generated at a rounded weak portion of the guide vane body made of CMC material, and the problem of thermal mismatch occurring during the fitting of the guide vane body and a metal component can be avoided; and a relatively large gap which may be generated between a CMC guide vane component and the metal component at a high temperature is eliminated.

IPC Classes  ?

• F01D 9/04 - NozzlesNozzle boxesStator bladesGuide conduits forming ring or sector
• F01D 9/02 - NozzlesNozzle boxesStator bladesGuide conduits

Abstract

A movable blade of a high-pressure turbine. A cooling unit is provided in the movable blade, and has cooling chambers which are in communication with an inner chamber via an impact hole. The cooling unit comprises at least one series-connection dual-wall cooling unit, which comprises a plurality of cooling chambers formed between an outer wall and an inner wall, wherein the plurality of cooling chambers communicate with each other sequentially. The impact hole comprises a first impact hole, the cooling chamber at a head end communicates with the inner chamber via the first impact hole, and the cooling chamber at a tail end communicates with the outside via an air film hole or a tail edge crack. The cooling unit is arranged in the movable blade of the high-pressure turbine, and configured to cool different areas in the movable blade. In addition, the cooling unit comprises at least one series-connection dual-wall cooling unit, and cold air sequentially flows through the plurality of cooling chambers in the movable blade, so as to increase a cold air flow path, such that a continuous impact jet flow is formed many times in the movable blade, thereby reducing the thermal load of the movable blade of the high-pressure turbine.

IPC Classes  ?

• F01D 5/18 - Hollow bladesHeating, heat-insulating, or cooling means on blades

Abstract

A rotor blade tip clearance control method and a rotor blade manufactured using same. The control method includes: coinciding, along an axial direction of an aircraft engine, a center of gravity of a rotor blade with a center of gravity of a rotor wheel disk supporting the rotor blade; rotating the rotor wheel disk to measure a leading edge deformation amount of the rotor blade; measuring a trailing edge deformation amount of the rotor blade; comparing the deformation amounts; and adjusting the center of gravity of the rotor wheel disk until the leading edge deformation amount tends to be approximately equal to the trailing edge deformation amount. The method can effectively improve or even solve the problem of inconsistent radial displacements of a leading edge and a trailing edge during the operation.

IPC Classes  ?

• F01D 11/22 - Actively adjusting tip-clearance by mechanically actuating the stator or rotor components, e.g. moving shroud sections relative to the rotor
• B23P 15/00 - Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
• B23P 15/02 - Making specific metal objects by operations not covered by a single other subclass or a group in this subclass turbine or like blades from one piece
• F01D 5/02 - Blade-carrying members, e.g. rotors
• F01D 5/14 - Form or construction
• F01D 11/14 - Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing
• F01D 21/00 - Shutting-down of machines or engines, e.g. in emergencyRegulating, controlling, or safety means not otherwise provided for
• F04D 19/00 - Axial-flow pumps specially adapted for elastic fluids
• F04D 27/00 - Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
• F04D 29/32 - Rotors specially adapted for elastic fluids for axial-flow pumps

Abstract

A water jet strengthening and polishing integrated system for blades of a bladed disk, comprising a vibration polishing unit and a water jet strengthening unit. The vibration polishing unit comprises a vibration polishing tank (3), a clamp (6) used for clamping a bladed disk being provided in the vibration polishing tank (3), and vibration motors (32) used for driving the vibration polishing tank (3) to vibrate being installed on the vibration polishing tank (3). The top ends of support springs (31) are fixedly connected to the vibration polishing tank (3), and the bottom ends of the support springs (31) are fixedly connected to a workbench (21). The water jet strengthening unit comprises a water jet strengthening device (5) used for carrying out water jet strengthening on blades of the bladed disk (7) and a driving mechanism used for clamping the water jet strengthening device (5) and driving same to move in any direction of space. The present invention further comprises a method, comprising: filling the vibration polishing tank (3) with an abrasive liquid; the vibration motors (32) driving the vibration polishing tank (3) to vibrate so as to polish the blades, and simultaneously, the driving mechanism driving the water jet strengthening device (5) to move so as to perform water jet strengthening successively on all the blades of the bladed disk (7). The present invention effectively improves the surface strengthening quality and efficiency for the blades of the bladed disk (7).

IPC Classes  ?

• B24B 31/06 - Machines or devices designed for polishing or abrading surfaces on work by means of tumbling apparatus or other apparatus in which the work or the abrasive material is looseAccessories therefor involving oscillating or vibrating containers
• B24C 1/04 - Methods for use of abrasive blasting for producing particular effectsUse of auxiliary equipment in connection with such methods for treating only selected parts of a surface, e.g. for carving stone or glass
• B24C 1/08 - Methods for use of abrasive blasting for producing particular effectsUse of auxiliary equipment in connection with such methods for polishing surfaces, e.g. by making use of liquid-borne abrasives
• B24C 5/04 - Nozzles therefor
• C21D 7/06 - Modifying the physical properties of iron or steel by deformation by cold working of the surface by shot-peening or the like

Abstract

An anti-spin blade, comprising a forward sweep centre of gravity stacking section, a trailing edge stacking section and a transition section, the forward sweep centre of gravity stacking section being formed by stacking along a forward sweep centre of gravity stacking line, the trailing edge stacking section being formed by stacking along a trailing edge stacking line, the transition section being located between the forward sweep centre of gravity stacking section and the trailing edge stacking section, and the transition section being formed via smooth transition of the forward sweep centre of gravity stacking section and the trailing edge stacking section. The anti-spin blade adopts a "forward sweep centre of gravity + trailing edge" composite stacking means to composite and superpose each modeling section, to form a three-dimensional blade, and the anti-spin blade is respectively stacked from two directions. The trailing edge stacking means used in the upper part increases the localized blade thickness, the localized strength margin is improved, an anti-spin function is achieved, and after a low-pressure turbine shaft is broken, the anti-spin blade can bear large impact loads.

IPC Classes  ?

• F04D 29/38 - Blades
• F01D 5/14 - Form or construction

Abstract

A blade platform, comprising a pair of side edges and a pair of bottom edges, wherein the side edge comprises a linear portion and a curved portion, wherein the linear portion comprises a first linear portion and a second linear portion, and the curved portion comprises a first curved portion and a second curved portion; wherein the first linear portion and the second linear portion are connected to two ends of the curved portion and are tangent to the curved portion, slopes of the first curved portion and the second curved portion are in the same direction and the first curved portion and the second curved portion are circumscribed. The benefits of the blade platform are that the problems of platforms pushing against each other and get stuck during the working state as in the prior art or lack of accuracy in the test results of the blade circumferential clearance test and the dynamic balance test can be avoided.

IPC Classes  ?

• F01D 5/22 - Blade-to-blade connections, e.g. by shrouding
• F01D 5/30 - Fixing blades to rotorsBlade roots

Abstract

The purpose of the present disclosure is to provide an ultrasonic detection method for a composite material part, comprising the following steps: using the same material and preparation process as a part to be detected to prepare comparison test blocks of multiple angles; determining the sound attenuation caused by a corresponding tilt angle according to the comparison test blocks of multiple angles, so as to obtain a compensation DAC correction curve; obtaining the best incident angle detected by a reflection method, the best incident angle detected by a penetration method, and the best reception angle detected by the penetration method; detecting the part by using the penetration method, and then detecting the part for a second time by using the reflection method. When detecting the slope, the detection sensitivity is adjusted according to the DAC correction curve. The ultrasonic detection method for a composite material part can improve the accuracy of performing detection on parts with complex shapes and structures.

IPC Classes  ?

• G01N 29/04 - Analysing solids

Abstract

A method for forming a forming part with an inclined surface and a forming part with an inclined surface wherein the forming method comprises: obtaining a model of the part to be formed; performing layer separating and slicing process to form a plurality of forming layers; a performing scanning path planning on each forming layer, wherein a suspended area and a non-suspended area are provided in a plurality of forming layers forming the inclined surface, frame scanning path comprises a first path and a second path, the first path corresponds to the non-suspended area and the second path corresponds to the suspended area; based on the size of the angle of inclination, setting process parameters for the first path and the second path, and printing layer by layer based on the set process parameters; wherein an energy density in the process parameters of the first path is smaller than an energy density in the process parameters of the second path. The forming method can ensure the angle of inclination of the inclined surface to form effectively.

IPC Classes  ?

• B23K 26/342 - Build-up welding
• B23K 26/082 - Scanning systems, i.e. devices involving movement of the laser beam relative to the laser head
• B23K 26/70 - Auxiliary operations or equipment

Abstract

A turbine guide vane structure, comprising a CMC component and a metal cover plate, the CMC component comprising an edge plate, and the edge plate being used for acting in concert with the metal cover plate; an axial force applying member is arranged between the edge plate and the metal cover plate, the axial force applying member being used for providing an axial pre-tightening force to the edge plate and the metal cover plate; at least a portion of an axial side surface of the edge plate comprises a notch, the notch comprising a first wall surface; at least part of the first wall surface is an inclined surface; an axial side surface of the metal cover plate acting in concert with said portion of the edge plate comprises a folding part used for acting in concert with the notch; the folding part comprises a side wall surface; the side wall surface is parallel to the first wall surface and is in surface-to-surface contact with the first wall surface. The turbine guide vane structure allows for keeping the metal component and the CMC component in close contact in an axial direction, thereby overcoming radial and axial expansion differences and guaranteeing installation stability.

IPC Classes  ?

• F01D 9/04 - NozzlesNozzle boxesStator bladesGuide conduits forming ring or sector
• F01D 9/02 - NozzlesNozzle boxesStator bladesGuide conduits

Abstract

Provided is a turbine guide vane structure. The structure comprises a CMC component and a metal cover plate. The CMC component comprises a blade body and an edge plate, the edge plate being matched with the metal cover plate. At least part of the axial side face of the edge plate comprises an edge plate flange, and at least part of the axial side surface of the metal cover plate matched with the edge plate comprises a cover plate flange, the edge plate flange being in contact with the cover plate flange in a surface-to-surface manner. The structure further comprises pins and an elastic member. The pins pass through at least part of the edge plate flange and the cover plate flange to be used for constraint between the edge plate flange and the cover plate flange. At least part of the pins further comprise extension ends used for attaching to a casing. The elastic member is sleeved on the outsides of at least part of the pins and is pressed between the edge plate flange and the cover plate flange which are connected by means of the at least part of the pins, so as to provide an axial pre-tightening force. The turbine guide vane structure can relieve the problem of thermal mismatching, has a simple whole structure, and reduces the structural complexity of components.

IPC Classes  ?

• F01D 5/14 - Form or construction
• F01D 9/04 - NozzlesNozzle boxesStator bladesGuide conduits forming ring or sector

Abstract

An adjustable stator blade position maintaining structure for an aero-engine compressor, which keeps an adjustable stator blade at a preset position when a compressor works. The adjustable stator blade position maintaining structure includes a positioning section, a limiting section and a force transmission section The positioning section is mounted in a mounting hole in a casing; the limiting section is cone-shaped and thus fits into a conical hole in the top of a journal of the adjustable stator blade; and the force transmission section is connected between the positioning section and the limiting section so as to transmit a load from the limiting section to the positioning section.

IPC Classes  ?

• F01D 17/16 - Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
• F04D 29/56 - Fluid-guiding means, e.g. diffusers adjustable

Abstract

A method for testing the strength performance of a metal material by means of instrumented indentation, relating to the technical field of material analysis and testing. An indentation tester is used for testing, and the method comprises the following steps: calibrating material parameters of an instrumented indentation test; establishing a functional relationship among hpile/hcx, n and hmax/R: hpile/hcx=f(n)*g(hmax/R), wherein hpile is an indentation depth when pile-up and sink-in effects are taken into consideration, hcxis an indentation depth when only elastic deformation is taken into consideration, n is a hardening index of a tensile test, hmax is the maximum indentation depth under the action of the maximum test force, and R is the radius of the ball indenter of the indentation tester; carrying out, by the indentation tester, the instrumented indentation test on a sample to be tested; and calculating the strength performance of the material of said sample according to the instrumented indentation test. A complete method for testing the strength performance of a metal material by means of instrumented indentation is provided, and by means of the method, the strength performance index of the material can be accurately obtained by using the result of the instrument indentation test.

IPC Classes  ?

• G01N 3/42 - Investigating hardness or rebound hardness by performing impressions under a steady load by indentors, e.g. sphere, pyramid

Abstract

A turbine guide vane mounting structure, comprising an upper cover plate, a lower supporting plate and a turbine guide vane located between the upper cover plate and the lower supporting plate. The turbine guide vane comprises an upper edge plate adapted to match the upper cover plate and a lower edge plate adapted to match the lower supporting plate. The structure further comprises a plurality of balls which are arranged between the upper edge plate and the upper cover plate and/or between the lower edge plate and the lower supporting plate. The upper cover plate and/or the lower supporting plate further comprises grooves, and the grooves are used for bearing the balls, so that rolling fit is formed between the upper cover plate and the upper edge plate and/or between the lower edge plate and the lower supporting plate. According to the structure, the thermal mismatch problem can be alleviated. Also provided is a turbine.

IPC Classes  ?

• F01D 9/02 - NozzlesNozzle boxesStator bladesGuide conduits
• F01D 5/00 - BladesBlade-carrying membersHeating, heat-insulating, cooling, or antivibration means on the blades or the members
• F01D 25/00 - Component parts, details, or accessories, not provided for in, or of interest apart from, other groups

Abstract

A turbine guide vane mounting structure, comprising a metal cover plate and CMC turbine guide vanes. The metal cover plate comprises at least one protrusion and at least one inclined surface, and exhaust slots are further formed in the inclined surface and the protrusion; each CMC turbine guide vane comprises an edge plate for matching the metal cover plate, and a blade body; the blade body comprises a hollow cavity; the position where the edge plate matches the inclined surface is a secondary inclined surface, and the position where the edge plate matches the protrusion is a plane or a cambered surface; relative dislocation can occur between the inclined surface and the secondary inclined surface, and between the protrusion and the plane or the cambered surface; a gap cavity is formed between the edge plate and the metal cover plate by means of the protrusion, and the gap cavity is communicated with the hollow cavity and the exhaust slots to serve as a circulation area of cooling gas. According to the turbine guide vane mounting structure, the thermal mismatch problem can be effectively relieved. Provided is a turbine, comprising the turbine guide vane mounting structure.

IPC Classes  ?

• F01D 9/04 - NozzlesNozzle boxesStator bladesGuide conduits forming ring or sector
• F01D 25/12 - Cooling

Abstract

A high-temperature single crystal alloy brazing material, comprising alloy powder and a binder, wherein the alloy powder comprises the following components by weight: 8%-18% of Cr, 3%-12.0% of Co, 1%-6% of W, 1%-6% of Ta, 2%-6% of Al, 0.5%-4.2% of Mo, 1%-5% of B, no more than 5% of Hf, and no more than 3% of Re, with the remainder being nickel and inevitable impurities. The high-temperature single crystal alloy brazing material has a low brazing temperature and a short welding process duration, so that thermal damage to a single crystal base material can be effectively reduced, and production efficiency is improved. The present invention further provides a high-temperature single crystal alloy brazing method.

IPC Classes  ?

• B23K 35/30 - Selection of soldering or welding materials proper with the principal constituent melting at less than 1550°C
• B23K 1/008 - Soldering within a furnace

Abstract

A turbine outer ring connection structure comprises a turbine outer ring, a middle-layer casing and a plurality of connection assemblies, wherein each connecting assembly comprises an elastic beam and a connection piece, the bottom of the elastic beam comprises an abutting part, and the abutting part abuts against an outer surface of the middle-layer casing so that a gap exists between other parts of the elastic beam and the middle-layer casing. A column body at one end of the connection piece passes out of the inner side of the middle-layer casing and is fixedly connected to the elastic beam via through holes in the middle-layer casing and the elastic beam, and the other end of the connection piece is connected to the turbine outer ring. The elastic beam provides stable pre-tightening force for the connection piece and the turbine outer ring by means of deformation, and the gap between the elastic beam and the middle-layer casing is used for absorbing the thermal deformation generated by the engine in the radial direction.

IPC Classes  ?

• F01D 25/04 - Antivibration arrangements
• F01D 25/24 - CasingsCasing parts, e.g. diaphragms, casing fastenings
• F01D 9/04 - NozzlesNozzle boxesStator bladesGuide conduits forming ring or sector
• F01D 25/28 - Supporting or mounting arrangements, e.g. for turbine casing

Abstract

An installation tool and installation method for fixing pins. In the mounting tool a cavity is provided in a tube body for accommodating a plurality of fixing pins. A first sliding groove and a second sliding groove are provided opposite each other and connected to the cavity. A first opening and a second opening are provided in two ends of the tube body. A pressing pin passes through the sliding grooves and is movably arranged on the tube body. The driving nut is adapted to driving the pressing pin to move towards the second opening.

IPC Classes  ?

• B25B 27/02 - Hand tools or bench devices, specially adapted for fitting together or separating parts or objects whether or not involving some deformation, not otherwise provided for for connecting objects by press fit or detaching same

Abstract

A fastening tool. In the fastening tool, a top part guiding matching portion engages a top part guiding portion in a sliding fit; a pressing part guiding matching portion engages a pressing part guiding portion in a sliding fit; a lever hinged to a base part; a transmission part engages a transmission part guiding slot in a sliding fit; the transmission part is driven to slide by the pressing part, and the lever is driven to rotate by the transmission part, then the top part is driven to slide out, due to a reaction force acting on the pressing part by the transmission part and the friction between the pressing part and the base part, the pressing part remains to be self-locked by friction, which can constrain the pressing part and the top part is locked.

IPC Classes  ?

• B23P 21/00 - Machines for assembling a multiplicity of different parts to compose units, with or without preceding or subsequent working of such parts, e.g. with programme control
• B23P 19/06 - Screw or nut setting or loosening machines

Abstract

A forming method and a forming part with a cantilever structure. The forming method includes: obtaining a model of the part to be formed, adding an inclined supporting portion to the cantilever structure, performing layer separating and slicing process on the model, performing scanning path planning on each forming layer. A suspended area and a non-suspended area are provided in a plurality of forming layers forming the inclined surface, frame scanning path includes a first path and a second path, the first path corresponds to the non-suspended area and the second path corresponds to the suspended area. Based on the size of the angle of inclination, setting process parameters for preparation for the first path and the second path, and printing layer by layer based on the set process parameters for preparation.

IPC Classes  ?

• B22F 5/00 - Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product
• B33Y 10/00 - Processes of additive manufacturing
• B33Y 80/00 - Products made by additive manufacturing

Abstract

An aero engine fuel metering device. The fuel metering device (2) comprises: a linear displacement sensor (21); and a validation curve memory unit, respectively in communication connection with the linear displacement sensor (21) and an engine electronic controller (3) of an aero engine fuel control system. The validation curve memory unit is configured to store a validation curve, and the validation curve is used for representing the relationship between adjusting and recording the voltage of the linear displacement sensor (21) and the fuel demand of an engine; after the engine electronic controller (3) is energized, the engine electronic controller (3) reads the validation curve stored in the validation curve memory unit, such that the validation curve in the engine electronic controller (3) is maintained consistent with the validation curve in the validation curve memory unit. An aero engine fuel control system, comprising the fuel metering device (2) and the engine electronic controller (3), and further comprising a fuel pump (1) and a fuel nozzle (4), the fuel metering device (2) being respectively connected to the fuel pump (1) and the fuel nozzle (4). The system has a validation memory function and a certain intelligent function, can maintain the consistency of the validation curve and eliminate the difference, thereby improving the matching and further improving the performance of the engine.

IPC Classes  ?

• G01F 9/00 - Measuring volume flow relative to another variable, e.g. of liquid fuel for an engine

Abstract

The present disclosure relates to a control method for winding deformation of fiber fabric and a forming mould thereof. The control method comprises step S1: lifting a plurality of positioning pins arranged on a surface of a forming mould according to a design position of a fiber fabric that is wound on the forming mould; step S2: winding the fiber fabric on the forming mould, and making a plurality of intersections of warp tracer yarn and weft tracer yarn, arranged on the fiber fabric, correspondingly cover on the positioning pins; step S3: retracting the lifted positioning pins; step S4: wrapping the fiber fabric with a fixing mould, and injecting resin after vacuumizing. The present disclosure provides a control method for winding deformation of fiber fabric and a forming mould thereof, ensuring that fiber deformations on the fiber fabric in the winding process meet the design requirements.

IPC Classes  ?

• B29C 70/44 - Shaping or impregnating by compression for producing articles of definite length, i.e. discrete articles using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding
• B29C 70/54 - Component parts, details or accessoriesAuxiliary operations
• B29C 70/22 - Fibrous reinforcements only characterised by the structure of fibrous reinforcements using fibres of substantial or continuous length oriented in at least two directions forming a two dimensional structure

Abstract

A forming powder for a forming part with a low tensile anisotropy by additive manufacturing, which can be used for forming the forming part with low tensile anisotropy, a method for forming a forming part with a low tensile anisotropy, and a forming part with a low tensile anisotropy. The forming powder for the forming part with low tensile anisotropy by additive manufacturing includes the following chemical components in terms of mass percentage (wt-%): 0.03%≤C≤0.09%, 20.50%≤Cr≤23.00%, 0.50%≤Co≤2.50%, 8.00%≤Mo≤10.00%, 0.20%≤W≤1.00%, 17.00%≤Fe≤20.00%, 0%

IPC Classes  ?

• C22C 19/05 - Alloys based on nickel or cobalt based on nickel with chromium
• B33Y 70/00 - Materials specially adapted for additive manufacturing
• B33Y 10/00 - Processes of additive manufacturing

Abstract

A forming powder for a forming part with a low high-temperature durability anisotropy by additive manufacturing, which can be used for forming the forming part with low high-temperature durability anisotropy, a method for forming a forming part with a low high-temperature durability anisotropy, and a forming part with a low high-temperature durability anisotropy. The forming powder is composed of the following chemical components in terms of mass percentage (wt-%): 0.03%≤C≤0.09%, 20.50%≤Cr≤23.00%, 0.50%≤Co≤2.50%, 8.00%≤Mo≤10.00%, 0.20%≤W≤1.00%, 17.00%≤Fe≤20.00%, 0%≤B≤0.002%, 0%≤Mn≤1.00%, 0.0375%≤Si≤0.15%, 0%≤O≤0.02%, 0%≤N≤0.015%, the rest are Ni and inevitable impurities; wherein 0.2≤C/Si≤1.0.

IPC Classes  ?

• C22C 19/05 - Alloys based on nickel or cobalt based on nickel with chromium
• B33Y 70/00 - Materials specially adapted for additive manufacturing

Abstract

The present disclosure provides a vibration exciting system and an apparatus for testing an aero-engine rotor, relating to the field of aero-engines, to improve the universality of the vibration exciting system. The vibration exciting system comprises a mounting ring, fixing parts, holders, guide rails, and nozzle assemblies. The mounting ring is configured to be annular; one ends of the fixing parts are fixedly connected to the mounting ring; the holders are slidably mounted at the other ends of the fixing parts, the plurality of holders being arranged circumferentially of the mounting ring; each guide rail connects two adjacent holders, connection positions of the guide rail and the holders being adjustable; and the nozzle assemblies are mounted on the holders. The radius size of a spraying area enclosed by the nozzle assemblies is adjusted by adjusting the positions of the holders on the fixing parts.

IPC Classes  ?

• G01M 7/02 - Vibration-testing
• G01M 15/02 - Details or accessories of testing apparatus
• G01M 15/14 - Testing gas-turbine engines or jet-propulsion engines

Abstract

A non-destructive testing method for lack-of-fusion (LOF) defects, and a testing standard part and a manufacturing method thereof, used for the non-destructive testing of LOF defects of an additive manufacturing workpiece. The manufacturing method of the LOF defect standard part comprises: step A, setting a LOF defect area of the standard part, in the LOF defect area, a proportion of the LOF defects in the LOF defect area is set as a first proportion value; step B, selecting an additive manufacturing forming process for manufacturing the LOF defect area to obtain a first process parameter of the additive manufacturing forming process corresponding to the first proportion value; step C, performing the additive manufacturing forming process based on the first process parameter to form the LOF defect area.

IPC Classes  ?

• B22F 10/85 - Data acquisition or data processing for controlling or regulating additive manufacturing processes
• B22F 10/28 - Powder bed fusion, e.g. selective laser melting [SLM] or electron beam melting [EBM]

Abstract

A non-destructive testing method for crack defects, and a testing standard part and a manufacturing method thereof, used for the non-destructive testing of crack defects of an additive manufacturing workpiece. The manufacturing method of the crack defect standard part comprises: step A, setting a crack defect area of the standard part, in the crack defect area, the proportion of the crack defects in the crack defect area is set as a first proportion value; step B, selecting an additive manufacturing forming process for manufacturing the crack defect area to obtain a first process parameter of the additive manufacturing forming process corresponding to the first proportion value; and step C, performing the additive manufacturing forming process based on the first process parameter to form the crack defect area. The non-destructive testing method for crack defects of the present invention has the advantages of accurate and reliable testing results.

IPC Classes  ?

• B22F 10/38 - Process control to achieve specific product aspects, e.g. surface smoothness, density, porosity or hollow structures
• G01N 23/04 - Investigating or analysing materials by the use of wave or particle radiation, e.g. X-rays or neutrons, not covered by groups , or by transmitting the radiation through the material and forming images of the material
• G01N 23/083 - Investigating or analysing materials by the use of wave or particle radiation, e.g. X-rays or neutrons, not covered by groups , or by transmitting the radiation through the material and measuring the absorption the radiation being X-rays
• G01N 23/18 - Investigating the presence of defects or foreign matter
• B23K 31/12 - Processes relevant to this subclass, specially adapted for particular articles or purposes, but not covered by any single one of main groups relating to investigating the properties, e.g. the weldability, of materials
• B22F 12/90 - Means for process control, e.g. cameras or sensors
• B33Y 50/00 - Data acquisition or data processing for additive manufacturing

Abstract

A method for preparing the prefabricated crack defects includes defining a defect area, defining a volume percentage of the crack defects in the defect area, adjusting the proportion of spherical powder, the proportion of hollow powder and process parameters of defect preparation according to the volume percentage of the crack defects, based on the technique of laser melting deposition, printing the defect area layer by layer by using the defect preparation powder and the process parameters of defect preparation, wherein the particle size of the defect preparation powder is between 45 μm and 150 μm, the proportion of spherical powder≥93% and the proportion of hollow powder<0.5%, the process parameters of defect preparation including: laser power of 450W-550W, scanning rate of 600 mm/min-1200 mm/min, powder feeding rate of 4 g/min-12 g/min, spot diameter of 1 mm-1.2 mm, scanning spacing of 0.5 mm-0.8 mm and layer thickness of 0.08 mm-0.2 mm.

IPC Classes  ?

• B22F 10/38 - Process control to achieve specific product aspects, e.g. surface smoothness, density, porosity or hollow structures
• B22F 10/28 - Powder bed fusion, e.g. selective laser melting [SLM] or electron beam melting [EBM]
• B22F 10/64 - Treatment of workpieces or articles after build-up by thermal means
• B22F 10/80 - Data acquisition or data processing
• B33Y 10/00 - Processes of additive manufacturing
• B33Y 40/20 - Post-treatment, e.g. curing, coating or polishing
• B33Y 50/00 - Data acquisition or data processing for additive manufacturing
• B23K 26/342 - Build-up welding

Abstract

A method for prefabricating pore defects by controlling a SLM process, including performing laser scanning on a specified metal melt layer (LY) according to a first scan path (P1) and a second scan path. The first scan path (P1) and the second scan path (P2) have a path overlap zone (A0), the path overlap zone (A0) has a predetermined width, and laser energy input superimposed in the path overlap zone (A0) is controlled to reach a predetermined energy value, whereby keyholes are formed at a plurality of positions in a lengthwise direction of the path overlap zone (A0), the specified metal melt layer (LY) is taken as a defect layer, and the keyholes in the path overlap zone (A0) is taken as pore defects.

IPC Classes  ?

• B22F 10/28 - Powder bed fusion, e.g. selective laser melting [SLM] or electron beam melting [EBM]
• B22F 10/366 - Scanning parameters, e.g. hatch distance or scanning strategy
• B22F 10/38 - Process control to achieve specific product aspects, e.g. surface smoothness, density, porosity or hollow structures
• B33Y 10/00 - Processes of additive manufacturing
• B33Y 50/02 - Data acquisition or data processing for additive manufacturing for controlling or regulating additive manufacturing processes

Abstract

A method for prefabricating a poor fusion defect by controlling a LMD process, including: obtaining a model, with a shaping zone and a defect prefabricated zone that has a preset defect; and performing a layerwise slicing process on the model. For each deposition layer of the defect prefabricated zone, the preset defect has a maximum dimension a0 in a perpendicular direction; for the shaping zone, performing a shaping process under predetermined shaping process parameters of the LMD process; and for the defect prefabricated zone, controlling shaping process parameters as follows: when a0

IPC Classes  ?

• B22F 10/37 - Process control of powder bed aspects, e.g. density
• B22F 10/85 - Data acquisition or data processing for controlling or regulating additive manufacturing processes
• B22F 10/28 - Powder bed fusion, e.g. selective laser melting [SLM] or electron beam melting [EBM]

Abstract

A method for preparing prefabricated gas pore defects includes: defining a defect area, defining a volume percentage of the gas pore defects in the defect area, adjusting the proportion of satellite powder, the proportion of hollow powder and the process parameters of defect preparation according to the volume percentage of the gas pore defects, based on the technique of laser melting deposition, printing the defect area layer by layer by using the defect preparation powder and the process parameters of defect preparation, wherein the particle size of the defect preparation powder is between 45 μm and 106 μm, the proportion of satellite powder is 55-65% and the proportion of hollow powder is 2.9-3.1%, the process parameters of defect preparation comprises: laser power of 600W-1000W, scanning rate of 400 mm/min-800 mm/min, powder feeding rate of 12 g/min-20 g/min, spot diameter of 1 mm-2 mm, scanning spacing of 0.5 mm-1 mm and layer thickness of 0.15 mm-0.2 mm.

IPC Classes  ?

• B22F 10/38 - Process control to achieve specific product aspects, e.g. surface smoothness, density, porosity or hollow structures
• B22F 1/0655 - Hollow particles
• B22F 1/05 - Metallic powder characterised by the size or surface area of the particles
• B22F 10/28 - Powder bed fusion, e.g. selective laser melting [SLM] or electron beam melting [EBM]
• B33Y 10/00 - Processes of additive manufacturing
• B33Y 50/02 - Data acquisition or data processing for additive manufacturing for controlling or regulating additive manufacturing processes
• B22F 9/08 - Making metallic powder or suspensions thereofApparatus or devices specially adapted therefor using physical processes starting from liquid material by casting, e.g. through sieves or in water, by atomising or spraying
• B22F 10/64 - Treatment of workpieces or articles after build-up by thermal means
• B33Y 40/20 - Post-treatment, e.g. curing, coating or polishing
• B22F 10/36 - Process control of energy beam parameters
• B22F 10/66 - Treatment of workpieces or articles after build-up by mechanical means
• B23K 26/342 - Build-up welding

Abstract

A low-cycle fatigue composite test device, comprising: a first chuck (20), a support (30), a lifting device, a rotating device, a horizontal movement device (40), a second chuck (50), and a load application device (60). The horizontal movement device (40) is fixed on the rotating device, and moves in the horizontal direction with respect to the support (30). The load application device (60) applies horizontal pushing force or pulling force to a blade by means of the horizontal movement device (40), the lifting device can apply vertical pulling force or pressure to the blade, and the rotating device can apply rotating force in different directions to the blade. The test device can apply external force in different directions to the blade, so as to realize bending, twisting, and multi-angle combined fatigue loading forms of the blade. By means of fatigue load and strain distribution, the test device can evaluate the structural performance of the blade under the fatigue load, so as to fully perform fatigue test on the blade.

IPC Classes  ?

• G01M 13/00 - Testing of machine parts

Abstract

A method for manufacturing a bi-material blade, an extrusion-suction integrated machine (400), and a bi-material blade. The method comprises the following steps: spreading a material layer (100) made of a first material (200); a suction head sucking away a first material (200) in a preset area (110) of the material layer (100); an extruder (410) extruding a second material (300) onto the preset area (110); setting a melting area (120), and melting and solidifying the first material (200) and/or the second material (300) in the melting area (120). The placement of material powder of two different materials on the same material layer (100) is realized, and the defect in the prior art whereby only one material can be spread on the same material layer (100) is thus solved.

IPC Classes  ?

• B22F 3/105 - Sintering only by using electric current, laser radiation or plasma
• B33Y 30/00 - Apparatus for additive manufacturingDetails thereof or accessories therefor
• B33Y 40/00 - Auxiliary operations or equipment, e.g. for material handling
• B33Y 10/00 - Processes of additive manufacturing
• B65G 33/26 - Screws
• B65G 53/24 - Gas suction systems
• B65G 53/36 - Arrangements of containers
• B65G 53/40 - Feeding or discharging devices
• B65G 53/10 - Gas pressure systems operating without fluidisation of the materials with pneumatic injection of the materials by the propelling gas
• B29C 67/00 - Shaping techniques not covered by groups , or

Abstract

The present application relates to the field of superalloy, disclosing a method for internal stress regulation in superalloy disk forgings by pre-spinning. The method includes: Step S1, determining a target revolution for regulating internal stress in the disk forgings, and determining a target deformation magnitude of plastic deformation required for regulating the internal stress by the pre-spinning of the disk forgings; and Step S2, performing the pre-spinning of the disk forgings by the target revolution, monitoring a deformation magnitude of the disk forgings, and stopping the pre-spinning when a monitored deformation magnitude of the disk forgings reaches the target deformation magnitude.

IPC Classes  ?

• C21D 8/02 - Modifying the physical properties by deformation combined with, or followed by, heat treatment during manufacturing of plates or strips
• C21D 9/40 - Heat treatment, e.g. annealing, hardening, quenching or tempering, adapted for particular articlesFurnaces therefor for ringsHeat treatment, e.g. annealing, hardening, quenching or tempering, adapted for particular articlesFurnaces therefor for bearing races
• C21D 11/00 - Process control or regulation for heat treatments
• G01L 5/00 - Apparatus for, or methods of, measuring force, work, mechanical power, or torque, specially adapted for specific purposes

Abstract

A vibration excitation device (10) and an oil-injection vibration excitation system. The vibration excitation device (10) comprises: a vibration excitation device body (1), the vibration excitation device body (1) comprising several adjustment units (11), all the adjustment units (11) being sequentially connected to each other, with the distance between adjacent adjustment units (11) being adjustable; a nozzle (2); and an adjustment assembly (3), with one end of the adjustment assembly (3) being connected to the vibration excitation device body (1), and the other end of the adjustment assembly (3) being connected to the nozzle (2). In the vibration excitation device (10), the distance between adjacent adjustment units (11) is adjustable, such that the length of the vibration excitation device (10) is adjustable, and accordingly, the positions of the adjustment assembly (3) and the nozzle (2) connected to the vibration excitation device body (1) are adjustable, so as to adapt to performance tests for aero-engines of different sizes, such that adjustment is convenient, thereby improving the test efficiency and economic benefits. The oil-injection vibration excitation system is used for a rotor system (20) of an aero-engine. The oil-injection vibration excitation system comprises an oil supply and return device (30) and the vibration excitation device (10), wherein the vibration excitation device (10) is mounted on a peripheral side of the rotor system (20) to allow the oil supply and return device (30) to be in communication with the nozzle (2).

IPC Classes  ?

• G01M 15/00 - Testing of engines
• G01M 7/02 - Vibration-testing

Abstract

A method for machining a part using a laser melting forming apparatus, comprising the following steps: establishing a function relation between height of a single channel and a defocusing amount; deriving an obtained function, respectively substituting different roots obtained by solving that a first derivative is equal to zero into a second derivative, obtaining numerical values of the roots of the first derivative corresponding to the numerical values that are smaller than zero among second derivative values, and recording the numerical value of the root thereof having a minimum absolute value as a first numerical value; respectively substituting numerical values of different roots obtained by solving that the second derivative is equal to zero into a third derivative, and recording the numerical values of the roots of the second derivative corresponding to the numerical values that are smaller than zero among the obtained third derivative values as second numerical values; and subtracting the first numerical value from the second numerical values, wherein the second numerical value corresponding to the numerical value in the obtained result that is smaller than zero and has the minimum absolute value is the value of the defocusing amount that can implement an optimal self-healing effect, such that an optimal parameter of the defocusing amount is obtained.

IPC Classes  ?

• B22F 10/28 - Powder bed fusion, e.g. selective laser melting [SLM] or electron beam melting [EBM]
• B22F 10/36 - Process control of energy beam parameters
• B22F 10/85 - Data acquisition or data processing for controlling or regulating additive manufacturing processes
• B33Y 10/00 - Processes of additive manufacturing
• B33Y 50/02 - Data acquisition or data processing for additive manufacturing for controlling or regulating additive manufacturing processes

Abstract

In order to alleviate a mismatch problem of thermal deformation, in all directions, of a connecting and installing structure between a CMC turbine outer annular component and a metal intermediate casing, a connector and an anti thermal mismatch connecting device are provided. The rod part of the connector comprises a subtractive hollow section and a cylindrical section. The subtractive hollow section is composed of a central shaft, a plurality of supporting rib plates extending outwards from a peripheral surface of the central shaft and inclined radially relative to the central shaft, and a plurality of outer annular plates arranged around the central shaft, with a circumferential gap between adjacent outer annular plates. The supporting rib plate is connected with the central shaft and the outer annular plate, and the central shaft is connected with the cylindrical section. The anti thermal mismatch connecting device the connector.

IPC Classes  ?

• F01D 11/08 - Preventing or minimising internal leakage of working fluid, e.g. between stages for sealing space between rotor blade tips and stator
• F16B 19/02 - Bolts or sleeves for positioning of machine parts, e.g. notched taper pins, fitting pins, sleeves, eccentric positioning rings
• F01D 25/24 - CasingsCasing parts, e.g. diaphragms, casing fastenings
• F01D 25/28 - Supporting or mounting arrangements, e.g. for turbine casing

Abstract

The present invention relates to a method for repairing an ultra-thin structure by means of additive manufacturing. The method comprises the following steps: removing a damaged region of an ultra-thin structure by means of machining; acquiring a three-dimensional model of a region to be repaired of the ultra-thin structure; processing the three-dimensional model of the region to be repaired; constructing a powder carrying device on the periphery of the bottom of the region to be repaired, and allowing powder in the powder carrying device to be filled until flush with or tangent to the surface of the bottom of the region to be repaired; melting, sintering or curing the powder in the powder carrying device around the outer contour of the ultra-thin structure by means of a high-energy beam or an auxiliary heating device, and combining the powder with the outer contour of the ultra-thin structure to form an outer contour thickened structure so as to form a flexible fixture; and repairing the region to be repaired by means of additive manufacturing technology according to a planned path obtained from the model processing. The present invention has the following beneficial technical effect: an ultra-thin structure can be repaired without requiring an extra-small-spot high-energy beam apparatus or a thickened fixture.

IPC Classes  ?

• B22F 3/105 - Sintering only by using electric current, laser radiation or plasma
• B22F 7/08 - Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting of composite workpieces or articles from parts, e.g. to form tipped tools with one or more parts not made from powder
• B22F 10/60 - Treatment of workpieces or articles after build-up
• B23P 6/00 - Restoring or reconditioning objects
• B33Y 40/00 - Auxiliary operations or equipment, e.g. for material handling

Abstract

A vibration excitation system and a test apparatus for testing an aero-engine rotor, relating to the field of aero-engines, and used for improving the universality of the vibration excitation system. The vibration excitation system comprises a mounting ring (1), a fixing member (2), supports (3), guide rails (4) and nozzle assemblies (5). The mounting ring (1) is configured to be annular; one end of the fixing member (2) is fixedly connected to the mounting ring (1); the support (3) is slidably mounted at the other end of the fixing member (2); a plurality of supports (3) are arranged in the circumferential direction of the mounting ring (1); the guide rail (4) is connected to two adjacent supports (3), and the connecting positions between the guide rail (4) and the supports (3) are adjustable; and the nozzle assembly (5) is mounted on the support (3). In the vibration excitation system, the radius of a jet area enclosed by the nozzle assemblies (5) is adjusted by adjusting the positions of the supports (3) on the fixing members (2), so as to adapt to test requirements of different aero-engines.

IPC Classes  ?

• G01M 7/02 - Vibration-testing

Abstract

The present disclosure provides a method of manufacturing a bonding structural test block with defects. The method of manufacturing the bonding structural test block with defects includes: providing a first plate and a second plate; applying an adhesive on an upper surface of the first plate to form an adhesive layer; heating and curing at least partial region of the adhesive layer for the first time; placing the second plate on the adhesive layer; and heating and curing the adhesive layer for the second time to form a boding structural test block. According to the present disclosure, the at least partial region of the adhesive layer is heated and cured for the first time and chemical reaction occurs, so that the at least partial region forms a defect, and controllable manufacturing of the defect is realized. The test block with the defect is subjected to mechanical detection to simulate the actual defective product. Furthermore, according to the method provided by the present disclosure, weak bond defect and kiss-bonds defect with different bonding strength are simulated by controlling the percentage of the at least partial region in the entire region of the adhesive layer.

IPC Classes  ?

• B32B 37/12 - Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by using adhesives
• G01N 29/30 - Arrangements for calibrating or comparing, e.g. with standard objects

Abstract

The present invention relates to a method for configuring a leading edge of a stator platform of a compressor, and a corresponding stator platform. Said configuration method comprises: simplifying the flowing of an airflow at the root of a rotor blade into the flowing of a free jet, and determining an airflow expansion angle according to the Mach number of the incoming flow at the root of a stator blade; calculating a radial height difference between a first end point on a leading edge of a stator platform and a trailing edge of an adjacent rotor platform by using an axial distance between the trailing edge of the adjacent rotor platform and the leading edge of the stator platform, the airflow expansion angle and a deviation coefficient; determining, on the basis of the radial height difference, the position of the first end point on the leading edge of the stator platform; determining the intersection point of the leading edge of the stator blade and the stator platform as the position of a second end point on the leading edge of the stator platform; and determining a profile line between the first end point and the second end point by bridging spline curves, so that the tail end of the profile line is tangent to the intersection line of the root of the stator blade and the stator platform, and the starting end of the profile line is kept on the same plane as the side wall of the leading edge of the stator platform.

IPC Classes  ?

• F04D 29/54 - Fluid-guiding means, e.g. diffusers
• F04D 29/16 - Sealings between pressure and suction sides

Abstract

A jet flow strengthening apparatus and method. The jet flow strengthening apparatus comprises a medium storage device (1), a mixing cavity (3), a nozzle (4), a lifting platform (7) and a control apparatus (8). A plurality of separated storage cavities (11) are arranged in the medium storage device (1), and graphene is disposed in at least one storage cavity (11). A first stirrer (12) is arranged in each of the storage cavities (11), and the storage cavities (11) are respectively in communication with the mixing cavity (3) via a jet flow channel (2). The mixing cavity (3) is respectively connected to the medium storage device (1) and the nozzle (4), and is internally provided with a second stirrer (31). The nozzle (4) has a hollow inner cavity and is in communication with the mixing cavity (3), and the nozzle (4) is located above the lifting platform (7). The control apparatus (8) respectively controls the operations of the first stirrer (12), the second stirrer (31) and the lifting platform (7). By means of the jet flow strengthening method, the strengthening of mixed jet flows of any liquid and graphene can be achieved.

IPC Classes  ?

• C21D 7/06 - Modifying the physical properties of iron or steel by deformation by cold working of the surface by shot-peening or the like
• C22F 1/00 - Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
• C22F 1/057 - Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon of alloys with copper as the next major constituent

Abstract

An objective of the present invention is to provide forming powder for additive manufacturing of a formed article having low stretching anisotropy, capable of forming the formed article having low stretching anisotropy. Another objective of the present invention is to provide a forming method for the formed article having low stretching anisotropy. Yet another objective of the present invention is to provide the formed article having low stretching anisotropy. In order to obtain the forming powder in the foregoing objective, the forming powder consists of the following chemical components in percentage by mass: 0.03％≤C≤0.09％, 20.50％≤Cr≤23.00％, 0.50≤Co≤2.50％, 8.00％≤Mo≤10.00％, 0.20％≤W≤1.00％, 17.00％≤Fe≤20.00％, 0％

IPC Classes  ?

• C22C 19/05 - Alloys based on nickel or cobalt based on nickel with chromium
• C22C 30/00 - Alloys containing less than 50% by weight of each constituent
• B22F 1/00 - Metallic powderTreatment of metallic powder, e.g. to facilitate working or to improve properties
• B22F 3/105 - Sintering only by using electric current, laser radiation or plasma
• B33Y 70/00 - Materials specially adapted for additive manufacturing
• B33Y 10/00 - Processes of additive manufacturing
• B33Y 40/20 - Post-treatment, e.g. curing, coating or polishing
• B33Y 80/00 - Products made by additive manufacturing

Abstract

A molding powder for additive manufacturing of a formed part with high-temperature persistence and low anisotropy, the formed part with high-temperature persistence and low anisotropy, and a method for forming the formed part. The molding powder for additive manufacturing of the formed part with high-temperature persistence and low anisotropy comprises the following chemical components in percentage by mass: 0.03%≤C≤0.09%, 20.50%≤Cr≤23.00%, 0.50≤Co≤2.50%, 8.00%≤Mo≤10.00%, 0.20%≤W≤1.00%, 17.00%≤Fe≤20.00%, 0%

IPC Classes  ?

• C22C 19/05 - Alloys based on nickel or cobalt based on nickel with chromium
• B22F 1/00 - Metallic powderTreatment of metallic powder, e.g. to facilitate working or to improve properties
• B22F 3/105 - Sintering only by using electric current, laser radiation or plasma
• B33Y 10/00 - Processes of additive manufacturing
• B33Y 70/00 - Materials specially adapted for additive manufacturing
• B33Y 80/00 - Products made by additive manufacturing

Abstract

Blade edge plates (6, 7, 8), a blade ring (100), an impeller disk, and a gas turbine engine. The blade edge plate (7) comprises a pair of side edges (71, 72) and a pair of bottom edges (73, 74); in the extension direction thereof, the first side edge (71) comprises a straight line segment (700) and an arc segment (800); the straight line segment (700) comprises a first straight line segment (701) and a second straight line segment (702); the arc segment (800) comprises a first arc segment (801) and a second arc segment (802); the first straight line segment (701) and the second straight line segment (702) are respectively connected to two ends of the arc segment (800), and are tangential to the arc segment (800); the slopes of the first arc segment (801) and the second arc segment (802) of the arc segment (800) are the same; and the first arc segment (801) and the second arc segment (802) are externally tangentially connected.

IPC Classes  ?

• F04D 29/26 - Rotors specially adapted for elastic fluids
• F04D 29/60 - MountingAssemblingDisassembling
• F01D 5/30 - Fixing blades to rotorsBlade roots
• F01D 5/14 - Form or construction

Abstract

A forming method for a formed part having an inclined surface and the formed part having an inclined surface. The forming method comprises: obtaining a model of a part to be formed; performing layered slicing processing on the model to form a plurality of formed layers (2a); planning a scanning path for each formed layer (2a), wherein there are a suspended area (20a) and a non-suspended area (21a) in each of the plurality of formed layers that constitute the inclined surface (10), a frame scanning path (12) is composed of a first path (121) and a second path (122), the first path (121) corresponds to the non-suspended area (21a), and the second path (122) corresponds to the suspended area (20a); setting preparation process parameters for the first path (121) and the second path (122) according to the size of an inclination angle; and printing layer by layer according to the set preparation process parameters. The energy density in the preparation process parameters for the first path (121) is less than the energy density in the preparation process parameters for the second path (122). The forming method can ensure that the inclination angle of the inclined surface can be effectively formed.

IPC Classes  ?

• B22F 3/105 - Sintering only by using electric current, laser radiation or plasma
• B23K 26/70 - Auxiliary operations or equipment
• B33Y 10/00 - Processes of additive manufacturing
• B33Y 80/00 - Products made by additive manufacturing
• B23K 26/342 - Build-up welding

Abstract

A forming part having a cantilever structure and a forming method therefor. The forming method comprises: obtaining a part model, adding an inclined support portion (1) to a cantilever structure (2), layering and slicing the model, and performing scanning path planning on a formed layer. In the formed layer forming an inclined plane (10), a layer to be formed has a suspended area (20a) and a non-suspended area (21a) which protrude out of the formed layer, and a frame scanning path is composed of a first path (121) and a second path (122), the first path (121) corresponding to the non-suspended area (21a), and the second path (122) corresponding to the suspended area (20a). Preparation process parameters are set for the first path (121) and the second path (122) according to an inclination angle, and printing is performed layer by layer according to the set preparation process parameters. The energy density in the preparation process parameter of the first path (121) is less than the energy density in the preparation process parameter of the second path (122). The present forming method can solve the problem of excessive supports for forming a part having a cantilever structure in a forming process.

IPC Classes  ?

• B22F 3/105 - Sintering only by using electric current, laser radiation or plasma

Abstract

An adjustable stator blade position maintaining structure (2) for an aero-engine compressor, which keeps an adjustable stator blade (3) at a preset position when a compressor works, thereby improving the pneumatic performance of the compressor. The adjustable stator blade position maintaining structure (2) comprises a positioning section (5), a limiting section (7) and a force transmission section (6), wherein the positioning section (5) is mounted in a mounting hole (11) in a casing (1); the limiting section (7) is cone-shaped and thus fits into a conical hole (12) in the top of a journal of the adjustable stator blade (3); and the force transmission section (6) is connected between the positioning section (5) and the limiting section (7) so as to transmit a load from the limiting section (7) to the positioning section (5).

IPC Classes  ?

• F04D 29/54 - Fluid-guiding means, e.g. diffusers

Abstract

BD1212D122). The method can effectively improve or even solve the problem of inconsistent radial displacements of a leading edge and a trailing edge during the operation of a rotor blade tip.

IPC Classes  ?

• F04D 29/32 - Rotors specially adapted for elastic fluids for axial-flow pumps
• F04D 29/38 - Blades

Abstract

A mounting tool (100) and mounting method for fixing pins (20). The mounting tool (100) comprises a tube body (110), a pressing pin (120) and a driving nut (140). A cavity (111) is provided in the tube body (110), and the cavity (111) is adapted to accommodating a plurality of fixing pins (20). A surface of the tube body (110) is provided with a first sliding groove (112) and a second sliding groove, which are provided opposite each other and are in communication with the cavity (111). A first opening (113) and a second opening (114), which are in communication with the cavity (111), are respectively provided in two ends of the tube body (110). The plurality of fixing pins (20) are adapted to entering the cavity (111) via the first opening (113) and exiting the cavity (111) via the second opening (114). The pressing pin (120) passes through the first sliding groove (112) and the second sliding groove and is movably arranged on the tube body (110), and at least part of the pressing pin (120) is exposed out of the surface of the tube body (110). The driving nut (140) is connected to the tube body (110) and is adapted to driving the pressing pin (120) to move towards the second opening (114).

IPC Classes  ?

• B25B 27/02 - Hand tools or bench devices, specially adapted for fitting together or separating parts or objects whether or not involving some deformation, not otherwise provided for for connecting objects by press fit or detaching same
• B23P 19/02 - Machines for simply fitting together or separating metal parts or objects, or metal and non-metal parts, whether or not involving some deformationTools or devices therefor so far as not provided for in other classes for connecting objects by press fit or for detaching same

Abstract

A propping tool (1), a bolt mounting device (200), and an assembly method for a high pressure compressor rotor (100). In the propping tool (1), a support (2) is provided with a propping member guide portion, an extrusion member guide portion (22), and a transmission member guide recess (23); a propping member (3) is provided with a propping member guide mating portion slidably matching the propping member guide portion; an extrusion member (4) is provided with an extrusion member guide mating portion (42) slidably matching the extrusion member guide portion (22); a lever (5) is hingedly connected onto the support (2); a transmission member (6) slidably matches the transmission member guide recess (23). The extrusion member (4) forces the transmission member (6) to slide, and the transmission member (6) drives the lever (5) to rotate to enable the propping member (3) to slide out. By means of the counteracting force acting on the extrusion member (4) by the transmission member (6), and the friction force between the extrusion member (4) and the support (2), the extrusion member (4) is in a frictional self-locking state, so that the extrusion member (4) is braked to lock the propping member (3).

IPC Classes  ?

• B23P 21/00 - Machines for assembling a multiplicity of different parts to compose units, with or without preceding or subsequent working of such parts, e.g. with programme control
• B23P 19/00 - Machines for simply fitting together or separating metal parts or objects, or metal and non-metal parts, whether or not involving some deformationTools or devices therefor so far as not provided for in other classes
• B25B 27/00 - Hand tools or bench devices, specially adapted for fitting together or separating parts or objects whether or not involving some deformation, not otherwise provided for
• B25B 11/00 - Work holders or positioners not covered by groups , e.g. magnetic work holders, vacuum work holders
• B23Q 3/06 - Work-clamping means

Abstract

A modeling method for a fan assembly includes-comprises constructing non-axially symmetric end wall curved surfaces in a cascade channel. Constructing the non-axially symmetric end wall curved surfaces in the cascade channel includes: determining, using a flow path design method for a dual flow path of a blade end area, an initial axially symmetric curve radius and a recessed curve lowest point radius of non-axially symmetric curved surfaces; and constructing the non-axially symmetric end wall curved surfaces in the cascade channel according to the initial axially symmetric curve radius and the recessed curve lowest point radius. The modeling method constructs the non-axially symmetric end wall curved surfaces in the cascade channel using the flow path design method for a dual flow path of a blade end area, to implement the control of flow directions by the non-axially symmetric curved surfaces, thereby reducing end wall loss.

IPC Classes  ?

• G06F 30/17 - Mechanical parametric or variational design
• F01D 5/14 - Form or construction
• F04D 29/38 - Blades
• G06F 111/10 - Numerical modelling

Abstract

The present invention relates to a method for controlling the winding deformation of a fiber fabric and a forming mold thereof. The control method comprises step S1: according to a design position of a fiber fabric wound on a forming mold, lifting several positioning pins disposed on a surface of the forming mold; step S2: winding the fiber fabric on the forming mold so that several intersecting points of a warp tracer yarn and a weft tracer yarn disposed on the fiber fabric correspondingly cover the positioning pins; step S3: retracting the lifted positioning pins; and step S4: covering the fiber fabric by using a fixed mold, and injecting a resin after vacuumizing. The present invention provides a method for controlling the winding deformation of a fiber fabric and a forming mold thereof to ensure that the fiber deformation of the fiber fabric at various places during a winding process meets design requirements.

IPC Classes  ?

• B29C 70/06 - Fibrous reinforcements only
• B29C 70/16 - Fibrous reinforcements only characterised by the structure of fibrous reinforcements using fibres of substantial or continuous length

Abstract

A manufacturing method for a bonding structure defect test block. The method comprises providing a first bonding plate and a second bonding plate (S101); laying an adhesive glue on an upper surface of the first bonding plate to form a glue layer (S102); performing a first heat curing on an at least partial area of the glue layer (S103); placing the second bonding plate onto the glue layer (S104); and performing a second heat curing on the glue layer to form a bonding structure test block (S105). By performing the first heat curing on the at least partial area of the glue layer and causing a chemical reaction, a defect is formed in the at least partial area, and the controllable manufacturing of the defect is realized. The test block with the defect is used to perform mechanical detection to simulate an actual defective product. Moreover, according to the manufacturing method, weak bond defects and kiss-bond defects having different bonding strengths are simulated by controlling the size of the at least partial area as a percentage of the entire area of the glue layer.

IPC Classes  ?

• G01N 29/30 - Arrangements for calibrating or comparing, e.g. with standard objects
• G01N 29/04 - Analysing solids
• G01N 1/28 - Preparing specimens for investigation

Abstract

A connecting member and an anti-thermal mismatch connecting device. A rod portion (24) of a connecting member (2) comprises a material-reducing hollow segment (21) and a cylindrical segment (22), the material-reducing hollow segment (21) consists of a central shaft (211), a plurality of supporting rib plates (212) extending outwards from the outer peripheral surface of the central shaft (211) and radially inclined relative to the central shaft (211), and a plurality of outer ring plates (213) arranged around the central shaft, and a circumferential gap (214) is provided between adjacent outer ring plates. The supporting rib plates (212) are connected to the central shaft (211) and the outer ring plates (213), and the central shaft (211) is connected to the cylindrical segment (22). During actual use, the anti-thermal mismatch connecting device can relieve the problem of thermal deformation mismatch of a connection mounting structure between a CMC turbine outer ring member and a metal interlayer casing in various directions.

IPC Classes  ?

• F01D 9/04 - NozzlesNozzle boxesStator bladesGuide conduits forming ring or sector
• F16B 39/24 - Locking of screws, bolts, or nuts in which the locking takes place during screwing down or tightening by means of washers, spring washers, or resilient plates that lock against the object

Abstract

A method for preparing a prefabricated crack defect, a method for preparing a built-in crack defect, and a prefabricated member (1). The method for preparing a prefabricated crack defect comprises: setting a defect area (10, 10a); setting the volume proportion of a crack defect in the defect area (10, 10a); on the basis of the volume proportion of the crack defect, adjusting the proportion of spherical powder, the proportion of hollow powder, and the defect preparation process parameters; and, on the basis of a laser melting deposition process, using defect preparation powder and the defect preparation process parameters to print the defect area (10, 10a) layer by layer; the particle size of the defect preparation powder is 45μm-150μm, the proportion of spherical powder is ≥93％, and the proportion of hollow powder is <0.5％; the defect preparation process parameters comprise: laser power 450W-550W, scanning rate 600mm/min-1200mm/min, powder feeding rate 4g/min-12g/min, light spot diameter 1mm-1.2mm, scanning spacing 0.5mm-0.8mm, and layer thickness 0.08mm-0.2mm.

IPC Classes  ?

• B22F 3/105 - Sintering only by using electric current, laser radiation or plasma
• B33Y 50/02 - Data acquisition or data processing for additive manufacturing for controlling or regulating additive manufacturing processes
• B33Y 40/00 - Auxiliary operations or equipment, e.g. for material handling
• B33Y 80/00 - Products made by additive manufacturing

Abstract

Disclosed is a method for prefabricating an air hole defect by means of a controlled SLM process, the method comprising performing laser scanning on a specified metal melt layer (LY) according to a first scan path (P1) and a second scan path (P2), with the first scan path (P1) and the second scan path (P2) having a path overlap area (A0), the path overlap area (A0) having a predetermined width, and laser energy input that is superimposed in the path overlap area (A0) being controlled to reach a predetermined energy value, whereby keyholes are formed at multiple positions in the lengthwise direction of the path overlap area (A0), with the specified metal melt layer (LY) being a defect layer, and the keyholes in the path overlap area (A0) being an air hole defect. The method can use a "keyhole effect" to form, in an SLM part, an air hole defect which has additive manufacturing metallurgical defect characteristics.

IPC Classes  ?

• B22F 3/105 - Sintering only by using electric current, laser radiation or plasma
• B33Y 10/00 - Processes of additive manufacturing
• B33Y 50/02 - Data acquisition or data processing for additive manufacturing for controlling or regulating additive manufacturing processes

Abstract

Disclosed are a non-destructive testing method for an incomplete fusion defect, and a testing standard part (10) and a manufacturing method therefor, which are used for non-destructive testing of an incomplete fusion defect of an additive manufacturing workpiece. The manufacturing method for an incomplete fusion defect standard part (10) comprises: step A, setting an incomplete fusion defect area (2) of a standard part (10), wherein in the incomplete fusion defect area (2), the proportion of an incomplete fusion defect in the incomplete fusion defect area (2) is set as a first proportion value; step B, selecting an additive manufacturing forming process for manufacturing the incomplete fusion defect area (2), and obtaining a first process parameter of the additive manufacturing forming process corresponding to the first proportion value; and step C, performing the additive manufacturing forming process on the basis of the first process parameter to form the incomplete fusion defect area (2). The non-destructive testing method for an incomplete fusion defect improves the accuracy and reliability of results of the non-destructive testing for the incomplete fusion defect of the additive manufacturing workpiece.

IPC Classes  ?

• G01N 1/28 - Preparing specimens for investigation
• G01N 1/44 - Sample treatment involving radiation, e.g. heat
• B22F 3/105 - Sintering only by using electric current, laser radiation or plasma
• B33Y 10/00 - Processes of additive manufacturing
• B33Y 40/00 - Auxiliary operations or equipment, e.g. for material handling

Abstract

Disclosed are a preparation method for a prefabricated air hole defect, a preparation method for a built-in air hole defect, and a prefabricated member (1) with the built-in air hole defect. The preparation method for a prefabricated air hole defect comprises: setting a defect area (10, 10a); setting the volume proportion of a air hole defect in the defect area (10, 10a); adjusting a satellite spherical powder proportion, a hollow powder proportion, and defect preparation process parameters according to the volume proportion of the air hole defect; and printing the defect area (10, 10a) layer by layer by using defect preparation powder and the defect preparation process parameters and on the basis of on a laser melting deposition process, wherein the particle size of the defect preparation powder is between 45 μm to 106 μm; in the defect preparation powder, the proportion of the satellite spherical powder is 55-65%, and the proportion of the hollow powder is 2.9-3.1%; and the defect preparation process parameters include: a laser power of 600 W to 1000 W, a scanning rate of 400 mm/min to 800 mm/min, a powder feed rate of 12 g/min to 20 g/min, a light spot diameter of 1 mm to 2 mm, a scanning interval of 0.5 mm to 1 mm, and a layer thickness of 0.15 mm to 0.2 mm.

IPC Classes  ?

• B22F 3/105 - Sintering only by using electric current, laser radiation or plasma
• B33Y 50/02 - Data acquisition or data processing for additive manufacturing for controlling or regulating additive manufacturing processes

Abstract

A method for prefabricating poor fusion defects by means of controlling an LMD process, wherein a model (10) that comprises a forming region (1) and a prefabricated defective region (2) is obtained, the prefabricated defective region (2) having a preset defect (3); the model (10) is subject to layered slicing processing, and for each deposited layer (4) of the prefabricated defective region (2), the preset defect (3) has the largest dimension a0 in the vertical direction; for the forming region (1), predetermined forming process parameters of the LMD process are used for forming; and for the prefabricated defective region (2), the forming process parameters are controlled as follows: when a0

IPC Classes  ?

• B33Y 10/00 - Processes of additive manufacturing
• B33Y 50/02 - Data acquisition or data processing for additive manufacturing for controlling or regulating additive manufacturing processes
• B22F 3/105 - Sintering only by using electric current, laser radiation or plasma

Abstract

A nondestructive testing method for crack defects, and a testing standard part and a manufacturing method therefor, used for nondestructive testing of crack defects in an additive manufactured workpiece. The manufacturing method for the crack defect standard part comprises: step A, setting a crack defect area of the standard part, and setting, in the crack defect area, the proportion of crack defects in the crack defect area as a first proportion value; step B, selecting an additive manufacturing forming process for manufacturing the crack defect area to obtain a first process parameter of the additive manufacturing forming process corresponding to the first proportion value; and step C, performing the additive manufacturing forming process on the basis of the first process parameter to form the crack defect area. The nondestructive testing method for crack defects has the advantage that the testing results are accurate and reliable.

IPC Classes  ?

• G01N 1/28 - Preparing specimens for investigation
• G01N 1/44 - Sample treatment involving radiation, e.g. heat
• B22F 3/105 - Sintering only by using electric current, laser radiation or plasma
• B33Y 10/00 - Processes of additive manufacturing
• B33Y 40/00 - Auxiliary operations or equipment, e.g. for material handling

Abstract

Disclosed are a balance shaft sleeve decomposition assembly (100), and a balance shaft sleeve decomposition method. The balance shaft sleeve decomposition assembly (100) comprises: an extension section (1) used for being fastened to the axial tail end of a rotation shaft (10) so as to extend the axial length of the rotation shaft (10); a top plate (2) axially positioned on the extension section (1) and provided with a plurality of mounting holes (22); and a plurality of decomposition screws (3) evenly distributed in the circumferential direction of the top plate (2), wherein the plurality of decomposition screws (3) penetrate the plurality of mounting holes (22) correspondingly and are in threaded connection with and fastened to at least some of a plurality of balancing machine reserved connectors (203), each decomposition screw (3) is provided with a first threaded section (31), and at least one part of the first threaded section (31) is in threaded connection with and fastened to the balancing machine reserved connectors (203); and extrusion members (4) fixedly connected to the decomposition screws (3), wherein the extrusion members can apply an axial extrusion force (F1) to the top plate (2) and are subjected to a counter-acting force (F2) of the extrusion force (F1), and the counter-acting force (F2) makes a balance shaft sleeve (20) separate from the rotation shaft (10). The decomposition assembly (100) has a good universality, and makes the balance shaft sleeve (20) simple in decomposition operation and easy to decompose.

IPC Classes  ?

• B25B 27/02 - Hand tools or bench devices, specially adapted for fitting together or separating parts or objects whether or not involving some deformation, not otherwise provided for for connecting objects by press fit or detaching same

Abstract

A low-pollution combustor and a combustion control method therefor. The low-pollution combustor includes a combustor head including a primary combustion stage and a precombustion stage, the primary combustion stage including a primary-combustion-stage channel and a primary-combustion-stage swirler disposed in the primary-combustion-stage channel. The primary combustion stage includes a pre-film plate disposed in the primary-combustion-stage channel, and the pre-film plate is radially divided into an outer-layer pre-film plate and an inner-layer pre-film plate. The positions and injection directions of fuel jet points of the primary combustion stage control fuel of the primary combustion stage to be injected into the primary-combustion-stage channel through primary-combustion-stage fuel jet orifices; and part of the fuel directly forms primary-combustion-stage direct-injection fuel spray, and the other part is hit on the pre-film plate close to an inner side of the primary-combustion-stage channel, or the two parts are respectively hit on the two layers of pre-film plates.

IPC Classes  ?

• F23R 3/30 - Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising fuel prevapourising devices
• F23R 3/28 - Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
• F23R 3/34 - Feeding into different combustion zones
• F23R 3/14 - Air inlet arrangements for primary air inducing a vortex by using swirl vanes

Goods & Services

Aeronautical engines; exhaust manifold for engines; engine mounts, other than for land vehicles; generators of electricity; speed governors for machines, engines and motors; propulsion mechanisms, other than for land vehicles; pistons for engines; motors, other than for land vehicles; starters for motors and engines; fuel filters (engine parts); transmissions, other than for land vehicles; hydraulic controls for machines, motors and engines; expansion tanks [parts of machines]; aeroplane engines; jet engines, other than for land vehicles; faucets [parts of machines, engines and motors]; freewheels, other than for land vehicles; torque converters, other than for land vehicles; gears, other than for land vehicles; shock absorbers for machines; hydraulic valves; emergency power generators. Voltage regulators for vehicles; simulators for the steering and control of vehicles; speed checking apparatus for vehicles; mileage recorders for vehicles; steering apparatus, automatic, for vehicles. Vehicle maintenance; airplane maintenance and repair; vehicle greasing; vehicle breakdown repair services; vehicle cleaning; replacement service of vehicle battery; rebuilding engines that have been worn or partially destroyed; rebuilding machines that have been worn or partially destroyed. Rental of navigational systems; piloting; packaging of goods; collection of recyclable goods [transport]; vehicle breakdown towing services; air transport; rental of aircraft engines; physical storage of electronically stored data or documents; storage of goods; warehousing. Vocational retraining; coaching [training]; educational services; arranging and conducting of colloquiums; arranging and conducting of workshops [training]; arranging and conducting of symposiums; providing online electronic publications [non-downloadable]; on-line publication of electronic books and journals; publication of books; publication of texts, other than publicity texts.

Goods & Services

Aeronautical engines; exhaust manifold for engines; engine mounts, other than for land vehicles; generators of electricity; speed governors for machines, engines and motors; propulsion mechanisms, other than for land vehicles; pistons for engines; motors, other than for land vehicles; starters for motors and engines; fuel filters (engine parts); transmissions, other than for land vehicles; hydraulic controls for machines, motors and engines; expansion tanks [parts of machines]; aeroplane engines; jet engines, other than for land vehicles; faucets [parts of machines, engines and motors]; freewheels, other than for land vehicles; torque converters, other than for land vehicles; gears, other than for land vehicles; shock absorbers for machines; hydraulic valves; emergency power generators. Transmitters of electronic signals; vehicle radios; voltage regulators for vehicles; simulators for the steering and control of vehicles; satellite navigational apparatus; speed checking apparatus for vehicles; navigational instruments; radar apparatus; sound locating instruments; global positioning system [gps] apparatus; mileage recorders for vehicles; naval signaling apparatus; anti-interference devices [electricity]; internal telecommunication apparatus; navigation apparatus for vehicles [on-board computers]; steering apparatus, automatic, for vehicles. Vehicle bumpers; aeronautical apparatus, machines and appliances; brake shoes for vehicles; directional signals for vehicles; vehicle joysticks; air vehicles; ejector seats for aircraft; aircraft; caps for vehicle fuel tanks; suspension shock absorbers for vehicles.

Goods & Services

Aeronautical engines; exhaust manifold for engines; engine mounts, other than for land vehicles; generators of electricity; speed governors for machines, engines and motors; propulsion mechanisms, other than for land vehicles; pistons for engines; motors, other than for land vehicles; starters for motors and engines; fuel filters (engine parts); transmissions, other than for land vehicles; hydraulic controls for machines, motors and engines; expansion tanks [parts of machines]; aeroplane engines; jet engines, other than for land vehicles; faucets [parts of machines, engines and motors]; freewheels, other than for land vehicles; torque converters, other than for land vehicles; gears, other than for land vehicles; shock absorbers for machines; hydraulic valves; emergency power generators. Voltage regulators for vehicles; simulators for the steering and control of vehicles; speed checking apparatus for vehicles; mileage recorders for vehicles; steering apparatus, automatic, for vehicles. Vehicle maintenance; airplane maintenance and repair; vehicle greasing; vehicle breakdown repair services; vehicle cleaning; replacement service of vehicle battery; rebuilding engines that have been worn or partially destroyed; rebuilding machines that have been worn or partially destroyed. Rental of navigational systems; piloting; packaging of goods; collection of recyclable goods [transport]; vehicle breakdown towing services; air transport; rental of aircraft engines; physical storage of electronically stored data or documents; storage of goods; warehousing. Vocational retraining; coaching [training]; educational services; arranging and conducting of colloquiums; arranging and conducting of workshops [training]; arranging and conducting of symposiums; providing online electronic publications [non-downloadable]; on-line publication of electronic books and journals; publication of books; publication of texts, other than publicity texts.

Goods & Services

Transmitters of electronic signals; vehicle radios; voltage regulators for vehicles; simulators for the steering and control of vehicles; satellite navigational apparatus; speed checking apparatus for vehicles; navigational instruments; radar apparatus; sound locating instruments; global positioning system [GPS] apparatus; mileage recorders for vehicles; naval signaling apparatus; anti-interference devices [electricity]; internal telecommunication apparatus; navigation apparatus for vehicles [on-board computers]; steering apparatus, automatic, for vehicles. Marketing studies; administration of consumer loyalty programs; business inquiries; compilation of statistics; providing business information via a web site; business management consultancy; business information; public relations; import-export agency services; marketing. Rental of navigational systems; piloting; packaging of goods; collection of recyclable goods [transport]; vehicle breakdown towing services; air transport; rental of aircraft engines; physical storage of electronically stored data or documents; storage of goods; warehousing. Vocational retraining; coaching [training]; educational services; arranging and conducting of colloquiums; arranging and conducting of workshops [training]; arranging and conducting of symposiums; providing online electronic publications [non-downloadable]; on-line publication of electronic books and journals; publication of books; publication of texts, other than publicity texts.

Goods & Services

Transmitters of electronic signals; vehicle radios; voltage regulators for vehicles; simulators for the steering and control of vehicles; electronic satellite navigational apparatus; speed checking apparatus for vehicles; electronic navigational instruments; radar apparatus; sound locating instruments for aircraft vehicles; global positioning system (GPS) apparatus; mileage recorders for vehicles; naval signaling apparatus; electric radio anti-interference devices for aircraft vehicles; internal telecommunication apparatus; on-board computers in the nature of navigation apparatus for vehicles; steering apparatus, automatic, for vehicles, namely, simulators for the steering and control of aircraft vehicles piloting; packaging of goods; collection and transport of recyclable bottles, cans, paper and cardboard; vehicle breakdown towing services; air transport; physical storage of electronically stored data or documents; storage of goods; warehousing providing online non-downloadable electronic publications in the nature of magazines in the field of aviation; electronic publishing services, namely, on-line publication of electronic books and journals of others in the field of aviation; publication of books; publication of texts, other than publicity texts

Goods & Services

Aeronautical engines; exhaust manifold for engines; engine mounts, other than for land vehicles; generators of electricity; speed governors for machines, engines and motors; propulsion mechanisms, other than for land vehicles; pistons for engines; motors, other than for land vehicles; starters for motors and engines; fuel filters (engine parts); transmissions, other than for land vehicles; hydraulic controls for machines, motors and engines; expansion tanks [parts of machines]; aeroplane engines; jet engines, other than for land vehicles; faucets [parts of machines, engines and motors]; freewheels, other than for land vehicles; torque converters, other than for land vehicles; gears, other than for land vehicles; shock absorbers for machines; hydraulic valves; emergency power generators. Vehicle bumpers; aeronautical apparatus, machines and appliances; brake shoes for vehicles; directional signals for vehicles; vehicle joysticks; air vehicles; ejector seats for aircraft; aircraft; caps for vehicle fuel tanks; suspension shock absorbers for vehicles.

Goods & Services

(1) Aeronautical engines; exhaust manifold for engines; engine mounts, namely mounting hangers adapted for exhaust systems for airplane engines; generators of electricity; speed governors for machines, engines and motors; propulsion mechanisms, namely kerosene airplane engines, turbofan engines for airplanes and helicopters; pistons for engines; electronic starter motors; starters for motors and engines; fuel filters (engine parts); transmissions for airplane engines; hydraulic controls, namely, hydraulic valves for machines, motors and airplane engines; hydraulic controls, namely, hydraulic couplers for machines, motors and airplane engines; expansion tanks [parts of machines]; aeroplane engines; jet engines, other than for land vehicles; freewheels for airplanes engines; torque converters, other than for land vehicles; transmission gears for industrial machinery; shock absorbers for machines; hydraulic valves being parts of machines; emergency power generators. (2) Faucets [parts of machines, engines and motors]. (3) Vehicle bumpers; support apparatus, machines and appliances for airplane engines, namely specially adapted parts for internal combustion engines; brake shoes for vehicles; directional signals for vehicles; vehicle joysticks; ejector seats for aircraft; aircraft; caps for vehicle fuel tanks; suspension shock absorbers for vehicles.

Abstract

Disclosed is a shaping method for a fan assembly. The shaping method comprises constructing non-axially symmetric end wall curves in a cascade channel. The constructing the non-axially symmetric end wall curves in the cascade channel comprises the following steps: determining, using a flow path design method for a dual flow path of a blade end area, an initial axially symmetric curve radius and a recessed curve lowest point radius of non-axially symmetric curves; and constructing the non-axially symmetric end wall curves in the cascade channel according to the initial axially symmetric curve radius and the recessed curve lowest point radius. The shaping method of the present invention constructs non-axially symmetric end wall curves in a cascade channel using a flow path design method for a dual flow path of a blade end area, so as to implement the control of non-axially symmetric curves on flow directions, thereby reducing end wall loss.

IPC Classes  ?

• G06F 17/50 - Computer-aided design

Abstract

An impeller tube-type nozzle for a gas turbine, with an inlet section, a retraction section and an outlet section. The inlet section is a section of annular channel, the retraction section comprises multiple gas flow channels separated by multiple blades, each gas flow channel is encircled by an outer peripheral wall face, an inner peripheral wall face, a suction face of one of two adjacent blades and a pressure face of the other of the two adjacent blades, and inlets of the gas flow channels have a fan-shaped cross section. For each gas flow channel, along the direction of gas flow from the inlet of the gas flow channel to the outlet the fan-shaped cross section gradually smoothly transitions into a circular cross section.

IPC Classes  ?

• F01D 9/04 - NozzlesNozzle boxesStator bladesGuide conduits forming ring or sector
• F01D 25/12 - Cooling
• F01D 9/02 - NozzlesNozzle boxesStator bladesGuide conduits
• F02C 7/18 - Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air

Abstract

A load reduction apparatus and method for a fan blade-out (FBO) event of an aero-engine, capable of bidirectionally adjusting the critical speed of a low pressure rotor even after the fuse part of the low pressure rotor fails under the action of an FBO load. The load reduction apparatus comprises a fuse part, a fan shaft, at least two sensors, and a controller. The fuse part is provided on a bearing block or a supporting cone wall of a first bearing. The fan shaft comprises an intelligent extendable structure. The at least two sensors are used for monitoring dynamic responses of the first bearing and a second bearing. The controller is disposed in association with the sensors and the intelligent extendable structure separately. The sensors detect abnormal dynamic responses of the first bearing and the second bearing, and transmit the detected dynamic responses to the controller. The controller sends a signal to the intelligent extendable structure so that said structure extends or retracts within a predetermined range, so as to change the length of the fan shaft.

IPC Classes  ?

• F02C 7/00 - Features, component parts, details or accessories, not provided for in, or of interest apart from, groups Air intakes for jet-propulsion plants
• F01D 21/14 - Shutting-down of machines or engines, e.g. in emergencyRegulating, controlling, or safety means not otherwise provided for responsive to other specific conditions
• F01D 25/16 - Arrangement of bearingsSupporting or mounting bearings in casings

Abstract

A low pollution combustor and combustion control method therefor. The low pollution combustor comprises a combustor dome (12), the combustor dome (12) comprises a main combustion stage (14) and a pre-combustion stage (15), and the main combustion stage (14) and the pre-combustion stage (15) are arranged together in a concentric manner; the pre-combustion stage (15) is in the center, and the main combustion stage (14) is arranged on the periphery of the pre-combustion stage (15); the main combustion stage (14) comprises a main combustion stage channel, a main combustion stage swirler (30) provided in the main combustion stage channel, and a pre-film plate (31); the pre-film plate (31) is divided into an outer-layer pre-film plate (31b) and an inner-layer pre-film plate (31a) in a radial direction. A position and a spraying direction of a fuel spaying point (25) of the main combustion stage (14) are configured to control main combustion stage fuel to be sprayed into the main combustion stage channel by means of main combustion stage fuel nozzle holes (25a, 25b), a part of the main combustion stage fuel forms main combustion stage direct spray oil mist, the other part is hit on the inner-layer pre-film plate (31a) close to the inner side of the main combustion stage channel, or is separately hit on the two layers of pre-film plates (31a, 31b). According to the low pollution combustor and control method therefor, the double layers of pre-film plates (31a, 31b) are coordinated with the position and the spraying direction of the fuel spaying point (25) in different working conditions, so that combustible mixed gases are distributed more evenly in a flame tube.

IPC Classes  ?

• F23R 3/28 - Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
• F23R 3/38 - Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising rotary fuel injection means
• F23R 3/34 - Feeding into different combustion zones
• F23R 3/58 - Cyclone or vortex type combustion chambers
• F23R 3/16 - Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration with devices inside the flame tube or the combustion chamber to influence the air or gas flow

Abstract

A method of manufacturing a metal reinforced rim of a composite material fan blade involves separately manufacturing three parts of a metal reinforced rim (20), including a first sidewall panel (201), a second sidewall panel (202) and a nose cone (203). In a manufacturing process, an inner side surface (201a) of the first sidewall panel and an inner side surface (202a) of the second sidewall panel are separately formed. After the first sidewall panel and the second sidewall panel have been connected, an outer side surface (201b) of the first sidewall panel and an outer side surface (202b) of the second sidewall panel are connected to form a processing surface (20B) for construction of the nose cone (203) of the metal reinforced rim. The invention eliminates an additional step for processing an inner surface of a metal reinforced rim, thereby significantly reducing the difficulties of processing the inner surface of the metal reinforced rim.

IPC Classes  ?

• F04D 29/38 - Blades

Abstract

Provided is a fan blade (10) for a turbofan engine. An interlayer in a thickness region of the fan blade (10) has an aramid honeycomb structure (11), such that layers of the fan blade (10) can be continuously laid. The fan blade eliminates a layer loss problem in a process of forming a fan blade with a laminated composite material, thereby reducing potential internal defects, ensuring rigidity of a blade while reducing a weight of the blade, increasing compression resistance of the blade, and enabling a forming process to be realized easily.

IPC Classes  ?

• F04D 29/38 - Blades
• B29C 70/00 - Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts

Abstract

A method for removing cracks on an inner cavity surface of a part formed by selective laser melting (SLM), comprising: a hot isostatic pressing treatment step: performing hot isostatic pressing on a part formed by SLM; and an abrasive flow machining step: performing abrasive flow machining on the part formed by SLM after the HIP treatment. The method above for removing cracks on an inner cavity surface of a part formed by SLM provides an abrasive flow machining step after the hot isostatic pressing step, the quality of the original surface of the part formed by SLM is relatively good; the use of the abrasive flow machining process eliminates open cracks on the inner cavity of the part, improving the comprehensive performance of the part.

IPC Classes  ?

• B22F 3/24 - After-treatment of workpieces or articles

Abstract

Disclosed is an impeller tube-type nozzle (101) for a gas turbine, comprising an inlet section (108), a retraction section (107) and an outlet section (106). The inlet section (108) is a section of annular channel, the retraction section (107) comprises multiple gas flow channels separated by multiple blades (105), each gas flow channel is encircled by a outer peripheral wall face (110), an inner peripheral wall face (111), a suction face of one of two adjacent blades (105) and a pressure face of the other of the two adjacent blades (105), and inlets (102) of the gas flow channels have a fan-shaped cross section. For each gas flow channel, along the direction of gas flow from the inlet (102) of the gas flow channel to the outlet (103) the fan-shaped cross section gradually smoothly transitions into a circular cross section. The outlet section (106) comprises circular pipelines (104) with axially non-varying diameters that correspond to each outlet (103) of the gas flow channels and are respectively connected. Compared with an impeller hole-type nozzle, in the impeller tube-type nozzle the number of blades can be significantly reduced without lowering performance.

IPC Classes  ?

• F02C 7/18 - Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
• F02C 7/12 - Cooling of plants
• F01D 9/02 - NozzlesNozzle boxesStator bladesGuide conduits

Abstract

Provided is an oil-gas separator, comprising a separation cavity and a rotary member for oil-gas separation, wherein the rotary member is arranged inside the separation cavity so that the separation cavity is divided into at least two levels of cavity via the rotary member; the at least two levels of cavity are in sequential fluid communication; and the cavity located the furthest upstream among the at least two levels of cavity is in fluid communication with a first cavity (a) having an oil-gas mixture, such that the oil-gas mixture, after flowing out of the first cavity (a), enters the at least two levels of cavity by means of the cavity located the furthest upstream such that perform oil-gas separation is carried out at least twice. The device enables the separation cavity to be divided into at least two levels of cavity by means of arranging the rotary member, such that the oil-gas mixture, after primary oil-gas separation is completed in one level of cavity, can enter another level of cavity for secondary oil-gas separation, thereby realizing performing oil-gas separation at least twice, and having a higher separation efficiency. Further provided are an oil-gas separation system and an aircraft engine.

IPC Classes  ?

• F01M 11/08 - Separating lubricant from air or fuel-air mixture before entry into cylinder

Abstract

An fusing structure and method of an aero-engine under a fan blade out load, wherein the aero-engine comprises a fan rotor (100), a stator part intermediate case (9), a first bearing (3) and a second bearing (4) supporting the fan rotor (100), a first support cone arm supporting the first bearing (3) on the stator part intermediate case (9), and a second support arm (13) supporting the second bearing (4) on the stator part intermediate case (9); the first support cone arm being of a thin-wall annular structure and comprising an upper cone arm (2) and a lower cone arm (1), the upper cone arm (2) has an upper junction surface (21), and the lower cone arm (1) has a lower junction surface (11); one of the upper junction surface (21) and the lower junction surface (11) is a concave spherical surface while the other one being a convex spherical surface; the upper junction surface (21) and the lower junction surface (11) are complementary and welded into a fusing structure with strength being lower than that of a parent material, the spherical surface center of the fusing structure being located at the axis (12) of the fan rotor (100).

IPC Classes  ?

• F01D 21/00 - Shutting-down of machines or engines, e.g. in emergencyRegulating, controlling, or safety means not otherwise provided for