A method for washing an aircraft engine including a compressor having variable guide vanes pivotable about respective spanwise axes and having a secondary air system in fluid communication with the compressor via a bleed outlet located downstream of the variable guide vanes, the method includes: injecting a washing fluid into the compressor of the aircraft engine; while the compressor is rotating at a rotational speed, pivoting the variable guide vanes about their respective spanwise axes to a purging position at which an air pressure at the bleed outlet is maximal for the rotational speed of the compressor; and after the injecting of the washing fluid, expelling the washing fluid out of the secondary air system by injecting air in the bleed outlet with the compressor being in rotation while the variable guide vanes are in the purging position.
A method is provided for operating an aircraft system. During this operating method, a plurality of drive units are provided that include a thermal engine drive unit and an electric machine drive unit. A mechanical load is powered using a first of the drive units. The first of the drive units includes a first rotating structure. A parameter of the first rotating structure is monitored. A failure of the first of the drive units is detected based on the monitored parameter. A switch is made from the first of the drive units to a second of the drive units to power the mechanical load where the failure of the first of the drive units is detected.
A rotating seal assembly of a gas turbine engine includes a rotating seal element, and a rotationally stationary seal support positioned radially outboard of the rotating seal element. The rotating seal element and the seal support are configured to define a seal interface therebetween. The seal element includes an axial pump portion defined by one or more axially and circumferentially extending grooves to urge an airflow therethrough. The airflow is configured to prevent a fluid from entering the seal interface. The axial pump portion defines a radial running clearance with a floating seal.
An environmental control system of a vehicle includes an inlet configured to receive a medium, an outlet for receiving a conditioned form of the medium. A first portion of the medium at the outlet is to be provided to a cabin of the vehicle, and a thermodynamic device is in fluid communication with the inlet. The thermodynamic device includes a compressor, a first turbine, and a second turbine, operably coupled by a shaft. At least a portion of the medium is provided to the compressor, the first turbine and the second turbine in series. An air-liquid heat exchanger is positioned fluidly downstream of the second turbine such that the medium output from the second turbine exchanges thermal energy with a flow of liquid at the liquid-air heat exchanger. The first portion of the medium is output to the cabin downstream of the liquid-air heat exchanger.
B64D 13/08 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being conditioned the air being heated or cooled
B64D 13/06 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being conditioned
A heat exchanger includes a heat exchanger inlet, a heat exchanger outlet, and a heat exchanger body. The heat exchanger body includes a plurality of heat exchanger tubes configured to direct a first fluid therethrough between the heat exchanger inlet and the heat exchanger outlet, and one or more mounts formed integral to and connected directly to at least one heat exchanger tube of the plurality of heat exchanger tubes. The one or more mounts are configured to secure the heat exchanger to one or more secondary components.
An apparatus and method for welding a thermoplastic composite component is provided. The apparatus includes a tool and a power source. The tool includes a heating device energized by the power source and a susceptor spaced from the heating device. The susceptor is configured for use in welding thermoplastic composite material and has a Curie temperature close to a susceptor temperature specified to be used during welding. The susceptor is disposed on the tool and includes a susceptor length extending longitudinally along the tool. The heating device is configured to induce an electromagnetic field within a susceptor length first portion and second portion. The heating device is configured to heat the first portion to the susceptor temperature and heat the second portion to a second temperature different than the susceptor temperature. The heating device longitudinally overlaps the first portion.
A method of performing thermal management of an energy storage device includes providing an energy storage device selectively connectable to an air conditioning system and including a plurality of individual cells. The method includes evaluating a temperature of the plurality of individual cells to determine a most relevant temperature parameter of the energy storage device, comparing the most relevant temperature parameter of the energy storage device to a desired operating temperature range of the energy storage device, and adjusting one or more parameters associated with the energy storage device in response to determining that the most relevant temperature parameter of the energy storage device is outside of the desired operating temperature range.
H01M 10/633 - Control systems characterised by algorithms, flow charts, software details or the like
H01M 10/48 - Accumulators combined with arrangements for measuring, testing or indicating the condition of cells, e.g. the level or density of the electrolyte
H01M 10/663 - Heat-exchange relationships between the cells and other systems, e.g. central heating systems or fuel cells the system being an air-conditioner or an engine
H02M 7/537 - Conversion of DC power input into AC power output without possibility of reversal by static converters using discharge tubes with control electrode or semiconductor devices with control electrode using devices of a triode or transistor type requiring continuous application of a control signal using semiconductor devices only, e.g. single switched pulse inverters
8.
HYBRID THERMAL MANAGEMENT METHOD FOR BATTERY INTEGRATED RESIDENTIAL HEAT PUMP
An air conditioning system includes a vapor compression loop including a compressor, an expansion device, a first heat exchanger, and a second heat exchanger. A working fluid is configured to circulate within the vapor compression loop. An electric energy storage device is selectively operable to supply power to a component of the air conditioning system. A thermal management system is associated with the electric energy storage device. The thermal management system includes a first heat transfer component and a second heat transfer component. The first heat transfer component is thermally coupled to the vapor compression loop during cooling of the electric energy storage device and the second heat transfer component is thermally coupled to the vapor compression loop during heating of the electric energy storage device.
H01M 10/6569 - Fluids undergoing a liquid-gas phase change or transition, e.g. evaporation or condensation
H01M 10/663 - Heat-exchange relationships between the cells and other systems, e.g. central heating systems or fuel cells the system being an air-conditioner or an engine
9.
THERMAL MANAGEMENT SYSTEM WITH FLUID CIRCUIT FOR ENERGY STORAGE DEVICE IN AIR CONDITIONING SYSTEM
A system includes an air conditioning system including: a first unit having a compressor and a first heat exchanger; a second unit having a second heat exchanger; the air conditioning system configured to circulate a refrigerant between the first unit and the second unit; an energy storage device configured to power the compressor; a controller; and a thermal management system having a third heat exchanger, the third heat exchanger configured to receive refrigerant from the air conditioning system in certain modes of operation; the thermal management system configured to supply fluid to the energy storage device to provide one of heating and cooling of the energy storage device.
H01M 10/663 - Heat-exchange relationships between the cells and other systems, e.g. central heating systems or fuel cells the system being an air-conditioner or an engine
A valve assembly for use in a rack cooling circuit includes a valve body having a first end, a second end, and a primary channel arranged within an interior of the valve body and extending between the first end and the second end. A first valve is associated with the valve body and is operable to control a flow through the valve body along the primary channel. A secondary channel is arranged within the interior of the valve body. The secondary channel is arranged at a non-parallel angle relative to the primary channel. An upstream end of the secondary channel is fluidly connected to the primary channel at a location downstream from the first valve. A second valve is associated with the valve body and is operable to control a flow through the secondary channel.
F16K 5/06 - Taps or cocks comprising only cut-off apparatus having at least one of the sealing faces shaped as a more or less complete surface of a solid of revolution, the opening and closing movement being predominantly rotary with plugs having spherical surfacesPackings therefor
F16K 5/08 - Taps or cocks comprising only cut-off apparatus having at least one of the sealing faces shaped as a more or less complete surface of a solid of revolution, the opening and closing movement being predominantly rotary Details
H05K 7/20 - Modifications to facilitate cooling, ventilating, or heating
An independent dehumidification element is provided. The independent dehumidification element includes pluralities of elements disposable in an airstream. The surface of at least one element of the plurality of elements includes an adsorbent coating. The adsorbent coating includes at least two or more solid adsorbents that differ from one another in one of a homogenous mixture and a heterogenous combination.
B01D 53/04 - Separation of gases or vapoursRecovering vapours of volatile solvents from gasesChemical or biological purification of waste gases, e.g. engine exhaust gases, smoke, fumes, flue gases or aerosols by adsorption, e.g. preparative gas chromatography with stationary adsorbents
B01D 53/28 - Selection of materials for use as drying agents
B01J 20/10 - Solid sorbent compositions or filter aid compositionsSorbents for chromatographyProcesses for preparing, regenerating or reactivating thereof comprising inorganic material comprising silica or silicate
B01J 20/22 - Solid sorbent compositions or filter aid compositionsSorbents for chromatographyProcesses for preparing, regenerating or reactivating thereof comprising organic material
F28F 13/18 - Arrangements for modifying heat transfer, e.g. increasing, decreasing by applying coatings, e.g. radiation-absorbing, radiation-reflectingArrangements for modifying heat transfer, e.g. increasing, decreasing by surface treatment, e.g. polishing
12.
ADAPTIVE CONTROLOF GRID-SERVICE ENABLED EQUIPMENT WITH INTEGRATED ENERGY STORAGE
According to embodiments, a cloud-native predictive control system includes a cloud-based (CB) controller that includes a processor and a memory. The CB controller is configured to perform CB controller operations that include electronically storing in the memory a grid-service schedule that includes scheduled future energy storage device (ESD) tasks of an ESD. The ESD is configured to selectively provide power to equipment. A predictive algorithm is executed to generate, based at least in part on a current ESD condition of the ESD, a predicted future ESD condition of the ESD. A first scheduled future ESD task is accessed from the scheduled future ESD tasks. Responsive to a determination by the predictive algorithm that the first scheduled future ESD task is in conflict with the predicted future ESD condition, a conflict resolution operation is executed.
A system includes an air conditioning system including: a first unit having compressor and first heat exchanger; a second unit having a second heat exchanger; the air conditioning system configured to circulate a refrigerant between the first unit and the second unit; an energy storage device; power electronics configured to power the compressor from the energy storage device; a controller; a thermal management system including: a pump configured to circulate liquid in a liquid circuit; a heat sink coupled to the liquid circuit and configured to cool the power electronics; a third heat exchanger, the third heat exchanger configured to receive refrigerant from the air conditioning system and the liquid in the liquid circuit; a fourth heat exchanger in thermal communication with the energy storage device and configured to receive liquid in the liquid circuit; a fifth heat exchanger configured to receive liquid in the liquid circuit; and a fan.
F24F 11/77 - Control systems characterised by their outputsConstructional details thereof for controlling the supply of treated air, e.g. its pressure for controlling air flow rate or air velocity by controlling the speed of ventilators
F24F 11/84 - Control systems characterised by their outputsConstructional details thereof for controlling the temperature of the supplied air by controlling the supply of heat-exchange fluids to heat-exchangers using valves
F24F 13/30 - Arrangement or mounting of heat-exchangers
14.
LIQUID COOLED THERMAL MANAGEMENT FOR BATTERY INTEGRATED RESIDENTIAL HEAT PUMP
An air conditioning system includes a vapor compression loop having a compressor, a first expansion device, a second expansion device, a first heat exchanger, a second heat exchanger, and a working fluid is configured to circulate within the vapor compression loop. An electric energy storage device is selectively operable to supply power to a component of the air conditioning system and a thermal management system is thermally and fluidly coupled to the vapor compression loop at a position between the first expansion device and the second expansion device. Expansion of the working fluid within at least one of the first expansion device and the second expansion device is controllable in response to a thermal demand of the electric energy storage device.
H01M 10/663 - Heat-exchange relationships between the cells and other systems, e.g. central heating systems or fuel cells the system being an air-conditioner or an engine
An air conditioning system has a vapor compression loop including a compressor, an expansion device, a first heat exchanger, and a second heat exchanger and a working fluid is configured to circulate within the vapor compression loop. An energy storage device is selectively operable to supply power to the air conditioning system and a thermal management system associated with the energy storage device. During operation of the vapor compression loop in a first mode, the thermal management system is thermally couplable to the vapor compression loop via a first bypass flow path and during operation of the vapor compression loop in a second mode, the thermal management system is thermally couplable to the vapor compression loop via a second bypass flow path.
H01M 10/663 - Heat-exchange relationships between the cells and other systems, e.g. central heating systems or fuel cells the system being an air-conditioner or an engine
An excessive attraction detection device is composed of a cylinder unit including pistons, and a magnet unit including a permanent magnet for attraction. The permanent magnet for attraction can be displaced integrally with the pistons between an attraction position and a retreat position. The attraction position separation energizing force acting on the pistons is larger than the magnetic force of mutual attraction between the permanent magnet for attraction and the workpiece when one workpiece is attracted and held by a workpiece attraction device and smaller than the magnetic force of mutual attraction between the permanent magnet for attraction and the workpiece when two workpieces are attracted and held by the workpiece attraction device.
A method of and tool for positionally aligning a gearbox of a gas turbine engine is provided. The method includes: providing an alignment tool that includes a plurality of probe pins and a support flange; attaching the alignment tool to an engine case of the gas turbine engine; engaging the gearbox with the engine case; positionally aligning the gearbox by contacting a first surface of the gearbox with a first probe pin of the plurality of probe pins, and contacting a second surface of the gearbox with a second probe pin of the plurality of probe pins; and securing the gearbox to the engine case while the first probe pin is in contact with the first surface of the gearbox and the second probe pin is in contact with the second surface of the gearbox.
A linear guide system for use in the assembly or disassembly of a gas turbine engine is provided. The gas turbine engine includes an engine shaft and an engine casing. The engine shaft is engaged with a compressor section and a turbine section and extends along an axial centerline. The engine casing has first and second engine casing segments that are axially separable from one another. The linear guide system includes a plurality of rail and guide block assemblies. Each rail and guide block assembly includes a rail head, a rail, and a guide block. The rail head is configured for attachment to the first engine casing. The guide block is configured for attachment to the second engine casing, and is configured to receive the rail in a manner that permits linear traverse of the rail relative to the guide block.
Hamilton Sundstrand Space Systems International, Inc. (USA)
Inventor
Rice, Cory R.
Thorne, Daniel
Mugurusa, Diego S.
Abstract
Microgravity dry-cleaning systems and rotary drums thereof are described. The microgravity dry-cleaning systems include a drum assembly having an inner drum and an outer drum and a cleaning solvent dispenser arranged within the inner drum and a drive assembly. The drive assembly is configured to rotationally drive the inner drum and the outer drum relative to the cleaning solvent dispenser and direct a cleaning solvent into the cleaning solvent dispenser for dispensing the cleaning solvent toward an interior surface of the inner drum.
A method for forming a thermoplastic part includes sulfonating a thermoplastic film by exposing the thermoplastic film to a sulfonation fluid to form a sulfonated thermoplastic film and forming the thermoplastic part with a plurality of stacked thermoplastic film layers. The plurality of stacked thermoplastic film layers include at least one sulfonated thermoplastic film layer of the sulfonated thermoplastic film and a plurality of unsulfonated thermoplastic film layers. The at least one sulfonated thermoplastic film layer forms a first exterior thermoplastic film surface of the thermoplastic part.
B32B 37/24 - Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by the properties of the layers with at least one layer not being coherent before laminating, e.g. made up from granular material sprinkled onto a substrate
B32B 38/00 - Ancillary operations in connection with laminating processes
C08J 7/043 - Improving the adhesiveness of the coatings per se, e.g. forming primers
21.
Clutch assembly for a hybrid-electric aircraft propulsion system
An aircraft propulsion system includes an engine, an electric machine, and a gearbox. The gearbox includes an output shaft, an electric machine drive gear, an engine drive gear, and a clutch assembly. The electric machine drive gear is mounted on the output shaft and driven by the electric machine. The engine drive gear is couplable with the output shaft by the clutch assembly. The clutch assembly includes a housing disk, a plurality of sliding pads, and a coupling piston disk. The housing disk is mounted on the output shaft and forms a plurality of apertures. The sliding pads are arranged circumferentially, each having a pad body portion extending through an aperture and including a first oblique side surface. The coupling piston disk includes a second oblique side surface radially coincident with the first and is movable to compress the sliding pads, coupling the output shaft with the engine drive gear.
B64D 35/022 - Transmitting power from power plants to propellers or rotorsArrangements of transmissions specially adapted for specific power plants for electric power plants of hybrid-electric type
F02C 7/36 - Power transmission between the different shafts of the gas-turbine plant, or between the gas-turbine plant and the power user
F16D 13/26 - Friction clutches with axially-movable clutching members with conical friction surfaces in which the or each axially-movable member is pressed exclusively against an axially-located member
A turbine exhaust duct (TED) for an aircraft engine, has: an annular inlet conduit extending around a central axis for directing combustion gases generally in an axial direction; outlet conduits communicating with the inlet conduit and extending generally radially outward relative to the inlet conduit, the outlet conduits extending from inlet ends at intersections with the inlet conduit to outlet ends, the outlet conduits having transition areas transitioning from a mainly axial direction to a mainly radial direction; and shielding conduits received into the outlet conduits, the shielding conduits overlapping the transition areas of the outlet conduits.
An apparatus is configured to selectively couple one of a first mechanical input and a second mechanical input to an electric machine. The apparatus includes a mechanical output configured to couple to a part of the electric machine. The apparatus also includes a sliding clutch configured to drive or be driven by the mechanical output. The apparatus further includes a selective actuator configured to move the sliding clutch in order to selectively control which mechanical input drives or is driven by the mechanical output. The second mechanical input is a gearbox configured to drive or be driven by an external mechanism.
F02C 7/36 - Power transmission between the different shafts of the gas-turbine plant, or between the gas-turbine plant and the power user
F02C 6/00 - Plural gas-turbine plantsCombinations of gas-turbine plants with other apparatusAdaptations of gas-turbine plants for special use
F16D 21/02 - Systems comprising a plurality of mechanically-actuated clutches for interconnecting three or more shafts or other transmission members in different ways
A data collection unit is provided for an aircraft propulsion unit. This data collection unit contains a dataset for use by a processing system to perform a method that includes: (A) trimming an actual operational parameter of the aircraft propulsion unit to provide a trimmed operational parameter of the aircraft propulsion unit for at least one of: (i) presenting to an operator of the aircraft propulsion unit; (ii) controlling operation of the aircraft propulsion unit; or (iii) monitoring the operation of the aircraft propulsion unit; and (B) converting the trimmed operational parameter to the actual operational parameter for use in determining an operational characteristic of the aircraft propulsion unit during a propulsion unit-inoperative event of a companion propulsion unit to the aircraft propulsion unit.
A computer-implemented method includes determining engine performance model parameters of the engine at desired operating conditions with zero humidity; determining additional energy flow out of the engine; and determining an exhaust plume temperature scaling factor. The method further comprises determining a contrail engine efficiency parameter (noverall_λ) based on additional energy flow out of the engine and the exhaust plume temperature scaling factor; and generating an improved Schmidt-Appleman equation based on the contrail engine efficiency parameter (noverall_λ). The method further includes determining an improved mixing line slope based on the improved Schmidt-Appleman equation; and determining the minimum humidity required for formation and persistence of contrails produced by the engine based on the improved mixing line slope.
A method may include determining, via a load sharing management operation of a controller, a target steady state load share for an associated one of a thermal engine or an electric motor system of a hybrid electric powertrain (HEP). The method may also include operating, by the controller, the associated one of the thermal engine or the electric motor system according to the target steady state load share. The method may also include determining, by the controller, that a measured load for the associated one of the thermal engine or the electric motor system does not meet the target steady state load share. The method may also include adjusting, by the controller, a control setting of the associated one of the thermal engine or the electric motor system, resulting in an adjusted load output of the associated one of the thermal engine or the electric motor system.
B60W 20/15 - Control strategies specially adapted for achieving a particular effect
B60W 20/13 - Controlling the power contribution of each of the prime movers to meet required power demand in order to stay within battery power input or output limitsControlling the power contribution of each of the prime movers to meet required power demand in order to prevent overcharging or battery depletion
28.
GAS TURBINE ENGINE WITH A SPLIT MIXED-FLOW TURBINE
A gas turbine engine is provided that includes a compressor section, a combustor, and a mixed-flow turbine. The mixed-flow turbine has a first turbine (“FT”) rotor stage, an annular first vane stage, and a second turbine (“ST”) rotor stage. The FT rotor stage includes an FT disk and a plurality of FT rotor blades extending outwardly from the FT disk. The ST rotor stage includes an ST disk and a plurality of ST rotor blades extending outwardly from the ST disk. The annular first vane stage includes a plurality of stator vanes that are distributed circumferentially, and disposed axially between the FT rotor stage and the ST rotor stage. One or more of the stator vanes includes a radially extending interior passage configured to permit a flow of cooling air to pass through the respective one or more stator vanes.
A propulsion system includes an engine, a drivetrain, and a propulsor. The engine includes an engine output shaft. The drivetrain is coupled with the engine output shaft. The drivetrain includes a propulsor output shaft, a gear assembly, and an electric motor assembly. The gear assembly includes a propulsor output gear mounted on the propulsor output shaft. The electric motor assembly includes a bevel gear assembly and an electric motor. The bevel gear assembly is rotatable about a second rotational axis. The bevel gear assembly is engaged with the propulsor output gear. The electric motor includes a rotor rotatable about a third rotational axis. The third rotational axis is oriented at an oblique angle relative to the second rotational axis. The rotor is engaged with the bevel gear assembly. The propulsor is interconnected with the propulsor output gear.
B64D 35/022 - Transmitting power from power plants to propellers or rotorsArrangements of transmissions specially adapted for specific power plants for electric power plants of hybrid-electric type
F16H 57/038 - Gearboxes for accommodating bevel gears
An aircraft propulsion system assembly includes a propulsion system and a control assembly. The propulsion system includes a propulsor, an engine, and an electrical assembly. The engine includes a rotational assembly coupled to the propulsor. The electrical assembly includes an electric motor coupled to the propulsor. The control assembly includes a propulsor sensor assembly, an electric motor sensor, channel A control units, and a channel B control unit. The channel A control units includes an engine control unit for the engine and an electric motor control unit for the electric motor. The channel B control unit is connected in signal communication with the propulsor sensor assembly, the electric motor sensor, the engine control unit, and the electric motor control unit.
B64D 31/18 - Power plant control systemsArrangement of power plant control systems in aircraft for electric power plants for hybrid-electric power plants
B64D 31/09 - Initiating means actuated automatically in response to power plant failure
B64D 35/022 - Transmitting power from power plants to propellers or rotorsArrangements of transmissions specially adapted for specific power plants for electric power plants of hybrid-electric type
B64D 43/00 - Arrangements or adaptations of instruments
B64D 45/00 - Aircraft indicators or protectors not otherwise provided for
31.
TWO-SPEED EPICYCLIC GEARBOX WITH CLUTCH FOR AIRCRAFT PROPULSION SYSTEM
An aircraft propulsion system is provided that includes a thermal engine, a gearbox, and a multiplate clutch. The gearbox includes an input shaft, an output shaft, an epicyclic gear arrangement, a drive gear, and a first layshaft assembly. The multiplate clutch is engaged with the first layshaft assembly. The epicyclic gear arrangement includes a sun gear, a plurality of planet gears, and a ring gear. The first layshaft assembly includes a first layshaft, a first layshaft input gear, and a first layshaft ring engagement gear. The first layshaft ring engagement gear is engaged with the ring gear, and the first layshaft input gear is engaged with the drive gear and the input shaft. The multiplate clutch is disposable in an disengaged configuration and in an engaged configuration.
F02C 7/36 - Power transmission between the different shafts of the gas-turbine plant, or between the gas-turbine plant and the power user
B64D 27/10 - Aircraft characterised by the type or position of power plants of gas-turbine type
F15B 15/14 - Fluid-actuated devices for displacing a member from one position to anotherGearing associated therewith characterised by the construction of the motor unit of the straight-cylinder type
F16H 3/46 - Gearings having only two central gears, connected by orbital gears
F16H 63/04 - Final output mechanisms thereforActuating means for the final output mechanisms a single final output mechanism being moved by a single final actuating mechanism
F16H 63/30 - Constructional features of the final output mechanisms
A method of monitoring a fuel nozzle of an aircraft engine includes supplying fuel to a combustor of the aircraft engine using the fuel nozzle during operation of the aircraft engine, and sensing an operating condition of the aircraft engine applicable to a duration during which the fuel nozzle is supplying fuel to the combustor. A machine learning algorithm is executed to associate the operating condition of the aircraft engine and the duration with a health degradation of the fuel nozzle. A servicing status for the fuel nozzle is annunciated based on the health degradation of the fuel nozzle.
This cylinder (10) comprises a cylinder tube (12), a head cover (14), a rod cover (16), a piston unit (26), and a tie rod (22). The cylinder tube (12) has an inner tube (12a) that forms a cylinder chamber (24), and an outer tube (12b) that covers the outside of the inner tube (12a) and forms a passage space (28) between the outer tube and the inner tube (12a). Guide protrusions (30, 32) protrude from at least one among the inner tube (12a) and the outer tube (12b) toward the passage space (28). The guide protrusions (30, 32) restrict the displacement direction of the tie rod (22) to only the axial direction, thereby facilitating assembly.
F15B 15/14 - Fluid-actuated devices for displacing a member from one position to anotherGearing associated therewith characterised by the construction of the motor unit of the straight-cylinder type
A connection device has a first joined body and a second joined body. The first joined body has an extension part that extends along an insertion/removal direction and that is inserted into an insertion hole formed in the second joined body. The outer peripheral surface of the extension part has a first step part and a second step part. The second step part is positioned farther inward than the first step part between the first step part and the base end of the extension part, the second step part engaging with the second joined body. The first step part engages with the second joined body after the engagement of the second step part is released.
F16L 37/084 - Couplings of the quick-acting type in which the connection between abutting or axially-overlapping ends is maintained by locking members combined with automatic locking
F16L 37/56 - Couplings of the quick-acting type for double-walled or multi-channel pipes
The Royal Institution for the Advancement of Learning/McGill University (Canada)
Inventor
Noronha Marques De Castilho, Bruno César
Larose, Joël
Makowiec, Mary E.
Stoyanov, Pantcho P.
Moreau, Christian
Sharifi, Navid
Chromik, Richard
Abstract
A method for applying a coating includes: providing a mixture of MCrAlY, Cu, Mo, and BaF2 powders; and spraying the mixture on a metallic substrate. A heat treating in an oxidizing atmosphere may form at least a surface layer of: BaCrO4; BaMoO4; CuTa2O6; Cu2O; and CuO. The substrate may form a seal such as a split ring seal.
An aircraft propulsion system is provided that includes a thermal engine, a gearbox, and a hydraulically actuated clutch system. The gearbox includes an input shaft, an output shaft, an epicyclic gear arrangement, a drive gear, and a first layshaft assembly. The clutch system includes a hydraulic coupling device engaged with the first layshaft assembly. The epicyclic gear arrangement includes a sun gear, planet gears, and a ring gear. The first layshaft assembly includes a first layshaft, a first layshaft input gear, and a first layshaft ring engagement gear. The first layshaft ring engagement gear is engaged with the ring gear, and the first layshaft input gear is engaged with the drive gear and the input shaft. The clutch system is disposable in an disengaged configuration and in an engaged configuration.
A cooling system for cooling one or more heat-generating devices includes a heat sink to which the one or more heat-generating devices are thermally coupled and a heat exchanger thermally coupled to the heat sink. The heat exchanger has a first flow path for receiving a primary cooling fluid and a second flow path for receiving a secondary cooling fluid. Heat is transferable to the primary cooling fluid from both the heat sink and the secondary cooling fluid at the heat exchanger.
An assembly for an aircraft powerplant includes a rotational load and a shaft. The shaft is coupled to the rotational load. The shaft extends along an axis between and to a first axial shaft end and a second axial shaft end. The shaft includes a slotted axial segment extending circumferentially about the axis. The slotted axial segment extends axially between and to a first segment end and a second segment end. The slotted axial segment has an outer diameter surface. The slotted axial segment forms a plurality of slots extending lengthwise through the slotted axial segment in an axial direction relative to the axis. The plurality of slots extend radially through the outer diameter surface. The plurality of slots are arranged as a circumferential array about the slotted axial segment.
A compact hybrid helicopter power plant includes a thermal engine including a rotatable output shaft, a main gearbox drivingly connecting the output shaft of the thermal engine to a main rotor of a helicopter, and an electric machine operable as a motor and as a generator drivingly connected to the output shaft of the thermal engine. The main gearbox has an input shaft drivingly connected to the output shaft of the thermal engine for common rotation with the output shaft of the thermal engine. A rotor of the electric machine is drivingly connected to the output shaft of the thermal engine for common rotation with the output shaft of the thermal engine. The thermal engine is disposed between the main gearbox and the electric machine.
B64D 35/022 - Transmitting power from power plants to propellers or rotorsArrangements of transmissions specially adapted for specific power plants for electric power plants of hybrid-electric type
An aircraft engine, has: an engine core including a compressor and a combustor; a casing defining a bleed port downstream of an inlet of the compressor and upstream of the combustor; a bleed air system connected to the bleed port and having: a bleed air conduit communicating with the bleed port and defining a bleed passage; and a connector connecting the bleed port to the bleed air conduit and extending from a port end at the bleed port to a conduit end at the bleed air conduit, the connector having a peripheral wall extending around a connector axis transversally intersecting the casing, the peripheral wall having an inner surface facing and exposed to the bleed passage, the inner surface defining ribs extending at least partially circumferentially around the connector axis, the ribs being axially distributed relative to the connector axis between the port end and the conduit end.
F02C 9/18 - Control of working fluid flow by bleeding, by-passing or acting on variable working fluid interconnections between turbines or compressors or their stages
F02K 3/02 - Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
Gas turbine engines include an engine core defining an engine axis and having compressor, combustor, and turbine sections arranged along the engine axis. A core flow path is defined through the sections of the engine core. A casing of the compressor section defines, in part, a portion of the core flow path, with a bleed air cavity defined between the casing of the compressor section and an engine housing. An impeller is arranged between the compressor and combustor sections, the impeller include an impeller shroud. A bleed aperture is defined axially between the casing and the impeller shroud with a bleed flow extension extending from the casing and into the bleed air cavity and a diffuser channel is defined between a surface of the bleed flow extension and a surface of the impeller shroud, with the diffuser channel having an inlet area that is less than an outlet area.
F01D 25/24 - CasingsCasing parts, e.g. diaphragms, casing fastenings
F02C 9/18 - Control of working fluid flow by bleeding, by-passing or acting on variable working fluid interconnections between turbines or compressors or their stages
F04C 14/20 - Control of, monitoring of, or safety arrangements for, machines, pumps or pumping installations characterised by varying the volume of the working chamber by changing the form of the inner or outer contour of the working chamber
45.
METHOD TO DECREASE COMPUTATIONAL COST ON AN N-DIMENSIONAL TABLE
A method includes obtaining at a first sampling time, a first set of n sampled values of n control parameters for one or more control systems of an aircraft. The method includes performing, in a higher power mode, a first sequential lookup and interpolation operation of a table maintained in the memory to obtain a first output control value, and sending, the first output control value to the one or more control systems of the aircraft. Determining that at least one condition associated with a first steady state has been satisfied and switching to a first lower power mode of the device. In the first lower power mode, performing a second sequential lookup and interpolation operation to obtain a second output control value and sending the second output control value to the one or more control systems of the aircraft.
An aircraft engine includes an annular gas path extending across a compressor and a turbine with a casing, a shroud and blades, a clearance defined between blade tips and the shroud. An active tip clearance control device directing a cooling airflow to the casing includes a first air source at a first temperature, a second air source at a second temperature greater than the first, a valve having first and second inlets connected to the sources and an outlet selectively connectible with the inlets. The outlet is fluidly connected to the casing to selectively direct the flow of cooling air from the first or second source. A sensor measures the clearance. A controller connected to the sensor receives a signal therefrom of a measured clearance, and generates commands causing the valve to open to the first or second source when the clearance is above or below a predetermined value.
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
G01M 1/36 - Compensating imbalance by adjusting position of masses built-in the body to be tested
48.
GAS TURBINE ENGINE WITH ROTATIONAL SPOOL BALANCING SYSTEM
F01D 11/08 - Preventing or minimising internal leakage of working fluid, e.g. between stages for sealing space between rotor blade tips and stator
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
An aircraft propulsion system is provided that includes a thermal engine and a gearbox. The gearbox includes an input shaft, an output shaft, a first epicyclic gear arrangement, a drive gear, and a first layshaft assembly. The first epicyclic gear arrangement includes a sun gear, a plurality of planet gears, and a ring gear. The sun gear is connected with the drive gear. The first layshaft assembly includes a first layshaft input gear, a first layshaft ring engagement gear, and a first clutch. The first layshaft ring engagement gear is engaged with the ring gear, and the first layshaft input gear is engaged with the drive gear and the input shaft. The first clutch is disposable in a clutch-disengaged configuration and in a clutch-engaged configuration.
F01D 25/06 - Antivibration arrangements for preventing blade vibration
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
53.
TORQUE MEASUREMENT BASED ON BEARING CONTACT ANGLE CONTROLLED BY GEAR FORCE REACTION
Torque measurement systems for aircraft propulsion systems include a gear assembly having a shaft and a bearing assembly configured to rotationally support the shaft within a housing. The bearing assembly includes an inner bearing raceway arranged on the shaft, an outer bearing raceway arranged on the housing, a rolling element arranged between the bearing raceways and configured to travel along a path defined between the bearing raceways, and a bearing cage arranged between the bearing raceways. The rolling element is configured drive rotational movement of the bearing cage. An axial load member is arranged to apply an axial load to the outer bearing raceway, a rotational velocity sensor is configured to measure a rotational velocity of the bearing cage, and a controller is configured to calculate a transferred toque of the gear assembly based on a detected rotational velocity of the bearing cage.
G01L 3/00 - Measuring torque, work, mechanical power, or mechanical efficiency, in general
G01L 5/12 - Apparatus for, or methods of, measuring force, work, mechanical power, or torque, specially adapted for specific purposes for measuring axial thrust in a rotary shaft, e.g. of propulsion plants
G01M 15/14 - Testing gas-turbine engines or jet-propulsion engines
54.
ACTIVE TIP CLEARANCE CONTROL SYSTEM FOR AIRCRAFT ENGINE
B01D 45/14 - Separating dispersed particles from gases or vapours by gravity, inertia, or centrifugal forces by centrifugal forces generated by rotating vanes, discs, drums or brushes
B64D 33/00 - Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for
F01M 11/00 - Component parts, details, or accessories, not provided for in, or of interest apart from, groups
57.
THE SEQUENCE IN WHICH SAFETY FUNCTIONS ARE ACTIVATED IN PROPELLER GOVERNORS OR CONTROLLERS TO MITIGATE UNDESIRABLE EFFECTS OCCURRING DURING FLIGHT
B64D 35/022 - Transmitting power from power plants to propellers or rotorsArrangements of transmissions specially adapted for specific power plants for electric power plants of hybrid-electric type
B64D 35/08 - Transmitting power from power plants to propellers or rotorsArrangements of transmissions characterised by the transmission being driven by a plurality of power plants
60.
METHOD AND APPARATUS FOR ENGINE HOT SECTION MAINTENANCE
B25B 23/02 - Arrangements for handling screws or nuts
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 27/14 - 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 assembling objects other than by press fit or detaching same
63.
SYSTEM AND METHOD FOR CLAMPING A COMPONENT OF AN AIRCRAFT ENGINE UNDERGOING A MANUFACTURING PROCESS
B64D 27/10 - Aircraft characterised by the type or position of power plants of gas-turbine type
B64D 35/022 - Transmitting power from power plants to propellers or rotorsArrangements of transmissions specially adapted for specific power plants for electric power plants of hybrid-electric type
F02C 7/36 - Power transmission between the different shafts of the gas-turbine plant, or between the gas-turbine plant and the power user
F16H 1/22 - Toothed gearings for conveying rotary motion without gears having orbital motion involving more than two intermeshing members with a plurality of driving or driven shaftsToothed gearings for conveying rotary motion without gears having orbital motion involving more than two intermeshing members with arrangements for dividing torque between two or more intermediate shafts
F16H 1/28 - Toothed gearings for conveying rotary motion with gears having orbital motion
A turbine exhaust duct for a gas turbine engine is provided that includes an exhaust manifold, an outer duct, first and second connecting panels, a first stiffener panel, and a second stiffener panel. The exhaust manifold includes an annular inlet and first and second exhaust ports. The outer duct includes a wall panel, an axial end aperture, a first lateral side aperture, and a second lateral side aperture. The first connecting panel includes a first exhaust port connecting flange and a first lateral side outer duct flange. The first stiffener panel has a periphery flange that is attached to the first connecting panel and to the outer duct wall panel. The second stiffener panel has a periphery flange that is attached to the first connecting panel and to the outer duct wall panel.
F01N 13/10 - Other arrangements or adaptations of exhaust conduits of exhaust manifolds
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
A centrifugal compressor includes an impeller rotatable about a central axis, and a scroll housing enclosing the impeller. The scroll housing includes a housing inlet configured to direct an airflow to the impeller for compression, and a scroll positioned downstream of an impeller outlet. The scroll is configured to direct a compressed airflow toward a housing outlet. A plurality of diffuser pipes are positioned in the scroll housing and are configured to direct the compressed airflow from the impeller outlet, through the plurality of diffuser pipes and into the scroll. An aerodynamic sleeve encloses at least one diffuser pipe of the plurality of diffuser pipes.
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
F04D 17/10 - Centrifugal pumps for compressing or evacuating
B32B 7/00 - Layered products characterised by the relation between layers Layered products characterised by the relative orientation of features between layers, or by the relative values of a measurable parameter between layers, i.e. products comprising layers having different physical, chemical or physicochemical properties Layered products characterised by the interconnection of layers
F01D 25/24 - CasingsCasing parts, e.g. diaphragms, casing fastenings
F01D 25/26 - Double casingsMeasures against temperature strain in casings
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
A double row stator assembly for a gas turbine engine includes a first vane row stator assembly that includes a plurality of first-row vanes, a second vane row stator assembly that includes a plurality of second-row vanes, and a wavy-edged flange configured to secure the first vane row stator assembly to the second vane row stator assembly when the first vane row stator assembly and second vane row stator assembly are assembled to form the double row stator assembly. The second vane row stator assembly is configured to be positioned to be sequentially downstream of the first vane row stator assembly when the first vane row stator assembly and the vane row second stator assembly are assembled to form the double row stator assembly such that trailing edges of the first-row vanes overlap leading edges of the second-row vanes.
F01D 1/04 - Non-positive-displacement machines or engines, e.g. steam turbines with stationary working-fluid guiding means and bladed or like rotor traversed by the working-fluid substantially axially
F16N 29/00 - Special means in lubricating arrangements or systems providing for the indication or detection of undesired conditionsUse of devices responsive to conditions in lubricating arrangements or systems
71.
ROTOR STAGE CONTAINMENT STRUCTURE FOR GAS TURBINE ENGINE
An annular containment structure for a rotor stage of a gas turbine engine is provided that includes an outer radial panel, a plurality of contact members, and a deformable structure. The outer radial panel has an inner radial surface and an outer radial surface. The contact members are distributed around a circumference of the containment structure. The deformable structure is engaged with the inner radial surface of the outer radial panel and the plurality of contact members. The deformable structure is configured to dissipate energy by plastically deforming. Each contact member includes an interior segment and an inner perimeter segment that are connected to one another. The inner perimeter segments form at least a portion of an inner radial surface of the containment structure.
F01D 25/24 - CasingsCasing parts, e.g. diaphragms, casing fastenings
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
A fir tree structure is provided and includes a part extending radially inwardly from a rotating part and having an inward taper. The part has a spline profile forming fixing lobes and necks, which are interleaved with the fixing lobes. The spline profile has constantly changing radii of curvature characterized in that the radii of curvature are relatively reduced in high stress locations and relatively increased in low stress locations.
An aircraft engine, has: an engine core including a compressor and a combustor; a casing defining a bleed port downstream of an inlet of the compressor and upstream of the combustor; a bleed air system connected to the bleed port and having: a bleed air conduit communicating with the bleed port and defining a bleed passage; and a connector connecting the bleed port to the bleed air conduit and extending from a port end at the bleed port to a conduit end at the bleed air conduit, the connector having a peripheral wall extending around a connector axis transversally intersecting the casing, the peripheral wall having an inner surface facing and exposed to the bleed passage, the inner surface defining ribs extending at least partially circumferentially around the connector axis, the ribs being axially distributed relative to the connector axis between the port end and the conduit end.
F02C 9/18 - Control of working fluid flow by bleeding, by-passing or acting on variable working fluid interconnections between turbines or compressors or their stages
78.
WIRELESS INTERFERENCE-FREE SECURE RECEIVE-ONLY DISCRETE CONTROL SOFTWARE
A method includes determining whether an aircraft is connected to an external power source and, if so, switching a wireless interface of the aircraft to a receive-only mode. The method also includes receiving, via the wireless interface at different times, beacon packets each containing encrypted authentication information. The method further includes performing a first authentication based on the encrypted authentication information and, responsive to performing the first authentication successfully, switching a test interface of flight control software of the aircraft to an enabled mode and performing a second authentication between the test interface and a source of the beacon packets. In addition, the method includes, responsive to performing the second authentication successfully, establishing a secure two-way wireless communication connection between the test interface and the source of the beacon packets and transmitting, via the secure two-way wireless communication connection, response packets from the test interface.
H04L 9/32 - Arrangements for secret or secure communicationsNetwork security protocols including means for verifying the identity or authority of a user of the system
A variable area nozzle assembly includes a fixed nozzle structure, a translating sleeve, a plurality of nozzle segments, and a plurality of segment hoop locking assemblies. The translating sleeve is movably mounted to the fixed nozzle structure. The translating sleeve is translatable along the nozzle axis within the fixed nozzle structure between and to a first axial position and a second axial position. The plurality of nozzle segments form a variable area nozzle extending circumferentially about the nozzle axis. Each nozzle segment of the plurality of nozzle segments is pivotably mounted to the translating sleeve. The plurality of nozzle segments includes a first nozzle segment and a second nozzle segment. The plurality of segment hoop locking assemblies include a first segment hoop locking assembly. The first segment hoop locking assembly includes a hoop crank. With the translating sleeve in the first axial position or the second axial position, the hoop crank restricts circumferential movement of the first nozzle segment relative to the second nozzle segment.
This application provides a screw compressor and a refrigeration system including the screw compressor. Specifically, the screw compressor including an economizer. A second muffler reaction chamber is disposed on an economizer pipeline, which connects the economizer and a compressor, at a position close to a first muffler reaction chamber, pressure pulsation in the economizer pipeline is mainly caused by a large pressure difference between a refrigerant gas in a compression chamber and a refrigerant gas in the economizer pipeline, by controlling a distance between the second muffler reaction chamber and the first muffler reaction chamber, after the pressure pulsation transmitted from the compression chamber of the compressor passes through the first muffler reaction chamber and the second muffler reaction chamber, good pressure pulsation attenuation can be achieved, an effective pulsation attenuation frequency range can be greatly widened to adapt to pressure pulsation generated by the compressor under different frequency conditions.
F04C 18/16 - Rotary-piston pumps specially adapted for elastic fluids of intermeshing-engagement type, i.e. with engagement of co-operating members similar to that of toothed gearing of other than internal-axis type with toothed rotary pistons with helical teeth, e.g. chevron-shaped, screw type
A system includes an air conditioning system including: a first unit having a compressor and a first heat exchanger; a second unit having a second heat exchanger; the air conditioning system configured to circulate a refrigerant between the first unit and the second unit; an energy storage device configured to power the compressor; a controller; a thermal management system having a third heat exchanger, the third heat exchanger configured to receive refrigerant from the air conditioning system in certain modes of operation to provide one of heating and cooling of the energy storage device.
A heat removal device operable to cool a heat-generating device includes a housing having a hollow interior and a base arranged within the hollow interior of the housing. The base includes a contact surface and a cooling surface. The contact surface is thermally couplable to the heat-generating device. At least one fin including a plurality of fin segments is arranged at the cooling surface. At least one of the plurality of fin segments includes a plurality of louvers.
A fuel system for an aircraft includes a cryogenic storage system for hydrogen fuel having an inner tank configured for direct contact with cryogenic hydrogen therein and an outer tank surrounding the inner tank and defined by a load-bearing element of the aircraft. The outer tank is spaced apart from the inner tank by an insulation gap. A first guided wave sensor array is coupled to the outer tank.
A Fabry-Pérot sensor assembly includes an optical element having a first end opposite a second end relative to a longitudinal axis of the Fabry-Perot sensor assembly. A first optical member is provided at the first end. A second optical member provided at the second end is a diaphragm that deflects more than the first optical member in response to pressure changes external to the optical element. An optical cavity is provided between the first end and the second end. A ring-shaped mirror is attached to a surface of the first optical member facing the second optical member. The ring-shaped mirror does not interfere with light propagation at an end of a bore that interfaces with the first optical member and configured to contain an optical fiber.
A valve device is provided with a nozzle that has a flow hole through which a fluid flows; a support member that supports the nozzle; a valve body that has a piezoelectric element and opens and closes an opening of the flow hole by driving of the piezoelectric element; and a position adjustment mechanism for adjusting the position of the nozzle with respect to the valve body. The position adjustment mechanism has an urging member for urging the nozzle toward the valve body; and a stopper member for preventing movement of the nozzle due to the urging member by coming into contact with the nozzle.
F16K 37/00 - Special means in or on valves or other cut-off apparatus for indicating or recording operation thereof, or for enabling an alarm to be given
A suction pad (10) comprises: a body (12) having a negative pressure chamber (20); and a sponge part (14) that is attached to an attachment surface (19) of the body and comes into contact with an object (W) to be suctioned. A plurality of connection holes (18a) for connecting the negative pressure chamber and the exterior are formed in the attachment surface. The sponge part contains a material having semi-open/semi-closed cells. One suction hole (26) connected to the plurality of connection holes, and an edge portion (28) surrounding the suction hole are formed in the sponge part. The height (H1) of the edge portion in the suction direction is longer than the height difference (H2) of the surface of the object to be suctioned.
[Problem] Disclosed is a transport implement with which it is possible to easily perform packing work. [Solution] A transport implement (10) according to the present invention comprises: a dunnage (11) placed on a pallet (80); and support members (20A, 20B) made of foamed resin that are placed on the dunnage (11) and that support cargo (90A, 90B) from below. Further, the support members (20A, 20B) are formed with a pair of first fork insertion holes (21) for lifting the support members (20A, 20B), a second fork insertion hole (22) for lifting the cargo (90A, 90B), and a first positioning recessed portion (26) that opens to outer surfaces and lower surfaces of the support members (20A, 20B). The dunnage (11) is formed with a first positioning protruding portion (16) that engages with the first positioning recessed portion (26) in a concave-convex manner and that is exposed from an outer surface opening (26K).
B65D 81/05 - Containers, packaging elements, or packages, for contents presenting particular transport or storage problems, or adapted to be used for non-packaging purposes after removal of contents specially adapted to protect contents from mechanical damage maintaining contents at spaced relation from package walls, or from other contents
B65D 19/44 - Elements or devices for locating articles on platforms
A lock unit (22) comprises: a first bush (28) through which a rod (20) extending in the axial direction is inserted; a second bush (30) which is disposed so as to be spaced apart from the first bush (28) in the axial direction and through which the rod (20) is inserted; and a lock mechanism (42) which presses a braking member against the rod (20) in the direction intersecting the axial direction between the first bush (28) and the second bush (30) so as to generate a holding force between the rod (20) and each of the first bush (28) and the second bush (30).
A clip-type connector includes: a base portion having a main surface; a wall portion extending upright from the base portion; a first elastic portion and a second elastic portion, the first elastic portion and the second elastic portion being located on a side of the wall portion opposite to the base portion and separated from each other in a direction along the main surface; a coupling portion that couples the first elastic portion and the second elastic portion, the coupling portion facing the main surface and being located on a side of the first elastic portion and the second elastic portion opposite to the wall portion; and a first extension portion between the first elastic portion and the second elastic portion, the first extension portion extending from the coupling portion toward the wall portion.
H01R 11/22 - End pieces terminating in a spring clip
H01R 4/18 - Electrically-conductive connections between two or more conductive members in direct contact, i.e. touching one anotherMeans for effecting or maintaining such contactElectrically-conductive connections having two or more spaced connecting locations for conductors and using contact members penetrating insulation effected solely by twisting, wrapping, bending, crimping, or other permanent deformation by crimping
H01R 4/48 - Clamped connectionsSpring connections using a spring, clip or other resilient member
H01R 43/027 - Apparatus or processes specially adapted for manufacturing, assembling, maintaining, or repairing of line connectors or current collectors or for joining electric conductors for connecting conductors by clips
90.
ADAPTIVE OVERHAUL WITH TWO BRAZE MATERIAL AND CT SCANS
A method of overhaul of a component includes comparing a component to reference data to provide additive manufacturing data. Depositing material on the component using an additive manufacturing device based upon the additive manufacturing data to provide a first object. The depositing of material includes initially depositing a first material having a relatively high melting point, and then depositing a second material which has a melting point lower than the relatively high melting point of the first material. The depositing step further including heating the first and second materials with a laser to sinter the materials to the component. Putting the component into the furnace for a heat cycle. Then determining predicted characteristics of the first object, and comparing the predicted characteristics of the first object to the reference data to provide machining data. Then machining the first object using the machining data. A system for overhauling a component is also disclosed.
An article has a nickel-based alloy substrate having, in weight percent: 5.4-7.4 Re; 4.1-5.9 Ru; 3.0-6.2 Cr; 3.0-10.0 Co; 0.5-3.8 Mo; 3.0-6.0 W; 4.6-8.6 Ta; 5.0-6.4 Al; 0.050-0.30 Hf; no more than 0.50 all other elements, if any, individually; and no more than 2.0 all other elements, if any, combined. A nickel-based coating is on the substrate and comprising, in weight percent: 6.0-10.0 Al; 4.0-15.0 Cr; 11.0-15.0 Co; 0.1-1.0 Hf; 0.1-1.0 Si; 0.1-1.0 Y; up to 1.0 Zr if any; up to 7.0 Ta if any; up to 6.0 W if any; no more than 1.0 all other elements, if any, individually; and no more than 4.0 all other elements, if any, combined.
C22C 19/05 - Alloys based on nickel or cobalt based on nickel with chromium
B22D 21/02 - Casting exceedingly oxidisable non-ferrous metals, e.g. in inert atmosphere
B32B 15/01 - Layered products essentially comprising metal all layers being exclusively metallic
B32B 15/04 - Layered products essentially comprising metal comprising metal as the main or only constituent of a layer, next to another layer of a specific substance
C22F 1/10 - Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of nickel or cobalt or alloys based thereon
C23C 14/02 - Pretreatment of the material to be coated
C23C 14/16 - Metallic material, boron or silicon on metallic substrates or on substrates of boron or silicon
C23C 14/32 - Vacuum evaporation by explosionVacuum evaporation by evaporation and subsequent ionisation of the vapours
C23C 28/00 - Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of main groups , or by combinations of methods provided for in subclasses and
C23C 28/02 - Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of main groups , or by combinations of methods provided for in subclasses and only coatings of metallic material
C23C 30/00 - Coating with metallic material characterised only by the composition of the metallic material, i.e. not characterised by the coating process
F01D 5/28 - Selecting particular materialsMeasures against erosion or corrosion
An engine for an aircraft includes a gear box, an engine oil system, a starter generator, and a starter generator cooling circuit. The gear box includes a gear assembly. The engine oil system includes an oil pump, a heat exchanger, and an oil tank forming an oil flow path of the engine oil system. The oil pump is coupled with the gear assembly. The oil pump is operable to pump an engine oil along the oil flow path through the heat exchanger to the oil tank. The heat exchanger includes a primary side and a secondary side. The primary side forms the oil flow path. The starter generator is coupled with the gear assembly. The starter generator cooling circuit has a coolant flow path formed by the secondary side and the starter generator.
A compact hybrid helicopter power plant includes a thermal engine including a rotatable output shaft, a main gearbox drivingly connecting the output shaft of the thermal engine to a main rotor of a helicopter, and an electric machine operable as a motor and as a generator drivingly connected to the output shaft of the thermal engine. The main gearbox has an input shaft drivingly connected to the output shaft of the thermal engine for common rotation with the output shaft of the thermal engine. A rotor of the electric machine is drivingly connected to the output shaft of the thermal engine for common rotation with the output shaft of the thermal engine. The thermal engine is disposed between the main gearbox and the electric machine.
An annular containment structure for a rotor stage of a gas turbine engine is provided that includes an outer radial panel, a plurality of contact members, and a deformable structure. The outer radial panel has an inner radial surface and an outer radial surface. The contact members are distributed around a circumference of the containment structure. The deformable structure is engaged with the inner radial surface of the outer radial panel and the plurality of contact members. The deformable structure is configured to dissipate energy by plastically deforming. Each contact member includes an interior segment and an inner perimeter segment that are connected to one another. The inner perimeter segments form at least a portion of an inner radial surface of the containment structure.
F01D 21/04 - Shutting-down of machines or engines, e.g. in emergencyRegulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator, e.g. indicating such position
F01D 25/24 - CasingsCasing parts, e.g. diaphragms, casing fastenings
95.
LATCH OPERATING ASSEMBLY FOR AN AIRCRAFT PROPULSION SYSTEM LATCH
A tool for operating a latch assembly includes a tool body, a tab, a first bumper, and a second bumper. The tool body extends lengthwise between a first tool end and a second tool end. The tool body further extends between a first lateral end and a second lateral end. The tool body forms a tool interface extending on a pivot axis. The pivot axis extends between the first lateral end and the second lateral end. The tab projects from the tool body at the first tool end. The first bumper projects from the tool body at a location between the first tool end and the second tool end. The second bumper projects from the tool body between the tab and the first bumper. The tab, the first bumper, and the second bumper project from a common side of the tool body.
A formation method is provided. During the method, a thermoplastic composite (TPC) skin and a lightning strike protection (LSP) layer are provided. The TPC skin is arranged with the LSP layer on a tool to provide a material stack, and the material stack is consolidated to form a consolidated TPC structure. A thin film (TF) layer on the consolidated TPC structure using a plasma treatment process. The LSP layer may be configured as or otherwise include LSP material, and the TF layer may include a TF material configured as or otherwise including an amine functional group or an epoxy functional group.
C23C 16/455 - Chemical coating by decomposition of gaseous compounds, without leaving reaction products of surface material in the coating, i.e. chemical vapour deposition [CVD] processes characterised by the method of coating characterised by the method used for introducing gases into the reaction chamber or for modifying gas flows in the reaction chamber
C23C 16/18 - Chemical coating by decomposition of gaseous compounds, without leaving reaction products of surface material in the coating, i.e. chemical vapour deposition [CVD] processes characterised by the deposition of metallic material from metallo-organic compounds
97.
Exhaust case for aircraft engine with stiffener reinforcement
An exhaust system for an aircraft engine, has: a turbine exhaust duct (TED) having an annular inlet conduit and outlet conduits extending generally radially outward relative to the annular inlet conduit; an exhaust case surrounding the TED, the exhaust case having openings, each of the outlet conduits received through a respective one of the openings; and exhaust conduits secured to the exhaust case and each extending around a respective one of the openings of the exhaust case, an exhaust conduit of the exhaust conduits including a duct protruding away from the exhaust case along a port axis and fluidly communicating with a respective one of the outlet conduits, a stiffener disposed radially outwardly of the duct relative to the port axis and extending away from the exhaust case, and a reinforcement member secured to the stiffener to increase an effective thickness of the stiffener.
A ball bearing assembly for an aircraft includes an inner race, a plurality of balls and an outer race positioned radially outwardly of the plurality of balls. The outer race is secured to a squirrel cage that will connect the outer race to static structure. The squirrel cage has a central axis that will be parallel to an axis of rotation of a rotating member to be supported by the balls. The squirrel cage has a plurality of recesses separated by beams. The beams have a radially inner surface and a radially outer surface defined relative to the rotational axis, and extend between axial ends and through an intermediate portion. The beams have a first radial thickness at the axial ends that is greater than a second radial thickness at the intermediate portion. A rotating assembly is also disclosed.
Methods and systems for assessing compliance of aircraft engines are described. The method comprises selecting a test population from a set of deployed aircraft engines based on one or more selection criteria, each of the deployed aircraft engines having associated thereto design requirements and field data; selecting at least one parameter that is present in both the design requirements and the field data of the test population, the design requirements comprising design time-series profiles, the field data comprising field time-series profiles; comparing the field time-series profiles to the design time-series profiles for the at least one parameter using a similarity metric to obtain field statistics; comparing the field statistics to expected statistics from the design requirements; and generating a compliance assessment output of the test population based on a difference between the field statistics and the expected statistics.
G06F 30/27 - Design optimisation, verification or simulation using machine learning, e.g. artificial intelligence, neural networks, support vector machines [SVM] or training a model
B64F 5/60 - Testing or inspecting aircraft components or systems
G06F 18/21 - Design or setup of recognition systems or techniquesExtraction of features in feature spaceBlind source separation
G06F 18/22 - Matching criteria, e.g. proximity measures
