The invention relates to a guide vane for a gas turbine, comprising an airfoil, a platform arranged at a radial end of the airfoil, an upstream flange extending radially from the platform, and a downstream flange extending radially from the platform, wherein the flanges, together with a section of the platform lying between the flanges, bound a groove extending in the circumferential direction of the gas turbine for the arrangement of a damping element. A surface of the section of the platform bounding the groove is arched radially at least in regions thereof in the direction of an opening of the groove. The invention further relates to a guide vane cluster, a housing for a gas turbine, as well as to a gas turbine.
The present invention relates to a method for inspecting a component of a turbomachine (1), in particular an aircraft engine, said method comprising the steps of: providing a sensor for detecting the component (20); moving the sensor along a sensor path relative to the component (35, 36); using the sensor to detect at least one region of the component (25, 26) that lies on the sensor path; wherein the sensor is moved in a robot-guided manner along the sensor path using control signals, and wherein the control signals are generated (55) based on AI.
A blading assembly (21) for a turbomachine, and to a turbomachine having improved flow characteristics. The blading assembly (21) has an endwall (1) on which a plurality of airfoils are formed adjacent one another, each airfoil (20) of the plurality of airfoils having a leading edge (2), a trailing edge (3), a chord (c), a pressure side (4), and a suction side (5); the endwall (1) having, between adjacent airfoils (20), a depression (11) in a region (6) of the pressure side (4) and a first thickened area (10) in a region (7) of the suction side (5). The first thickened area (10) begins at a point at least 10% of the chord (c) away from the leading edge (2).
The invention relates to an axially divided inner ring as well as a variable vane cascade for an aircraft engine. The inner ring and the vane cascade improve the efficiency of the aircraft engine in that differently formed vanes and/or vane mounts are formed respectively in the inner ring or in the vane cascade.
Avane actuating arm (10) for a turbomachine, the vane actuating arm (10) including two legs (12) which are pivotable relative to each between at least one open position and a closed position and form a clamping device having at least one clamping surface (14) on each of the legs (12). In the closed position, a vane stem (20) provided for varying the pitch of a stator vane of the turbomachine can be frictionally held between the two legs (12) via the two clamping surfaces (14), forming a clamping connection (16). Each of the legs (12) has an opening (50), the openings (50) overlapping each other in the closed position such that a through-bolt connectable to an actuating element of the turbomachine for controlling an angular position of the vane stem (20) can be passed through the openings (50).
The present invention relates to a method for supporting the examination of a component for a turbomachine, in particular for an aircraft engine, comprising the steps of: providing a USB camera; capturing of an image of the component by means of the USB camera while the USB camera is held by hand; comparing and combining the image, which shows an examination site of the component, with a computer model of the component; marking the examination site in the computer model combined with the image and thus determining coordinates of the examination site in the computer model.
The invention relates to a rotor blade (1) for a blisk (2) of a fluid machine (3), comprising a blade (4) and a blade root (5) said rotor blade being particularly lightweight and stable. The rotor blade (1) is characterized in that the blade (4) comprises at least one main part (6) which consists of a base material with a lower density than the metal or metal alloy of the blade root (5). The blade (4) and the blade root (5) are connected together in a transition region (9) between the blade (4) and the blade root (5). The blade root (5) forms metal fibers (10) in the transition region (9), said metal fibers being used to bond the blade root (5) to the transition region (9).
50607070) performing a measurement on the component by means of the sensor assembly in the measurement position, wherein the measurement is performed and/or analyzed on the basis of the identified measurement position.
The invention relates to an air conduction system for an aircraft engine with a primary flow channel and a branch channel, in which, in particular, the branch channel can be a secondary flow channel and/or a bleed air channel, wherein the branch channel branches off the primary flow channel at a connecting region, comprising a closing device arranged at or in the connecting region for separating the branch channel from the primary flow channel, wherein the closing device has at least one closing ring for closing the connecting region.
A stator vane assembly (10) and a method for assembling a stator vane assembly (10) of a turbomachine, the stator vane assembly (10) including a plurality of variable stator vanes (11) whose stator vane platform (12) has a stator vane trunnion (13) that is mounted in a receiving opening (14) of a casing (15) of the turbomachine; a stator vane head (16) of the stator vane (11) having a bearing trunnion that is mounted on an inner ring (19) disposed on a rotor (119) of the turbomachine. In the method, a stator vane trunnion (13) disposed on a stator vane platform (12) of a stator vane (11) is inserted into a receiving opening (14) of a casing (15), which receiving opening (14) is disposed radially with respect to a rotor axis of the turbomachine, and an inner ring (19) is provided on a rotor (119) of the turbomachine.
The invention relates to a pivoting apparatus (10) for a component (11), in particular of a turbomachine (1), comprising: a suspension device (14) which is movable along a leveling axis (N) for arranging the pivoting apparatus (10) on a holding apparatus (20); and a receiving device (15) which is rotatable about a pivot axis (S) and can be connected to the component (11), wherein the suspension device (14) is movable along the leveling axis (N).
B66C 1/24 - Single members engaging the loads from one side only
B66C 13/08 - Auxiliary devices for controlling movements of suspended loads, or for preventing cable slack for depositing loads in desired attitudes or positions
F01D 25/28 - Supporting or mounting arrangements, e.g. for turbine casing
12.
METHOD FOR CHECKING A COMPONENT FOR A TURBOMACHINE
The present invention relates to a method for checking a component (45) for a turbomachine (1), in particular an aircraft engine (5), comprising the following steps: i) providing (81) a plenoptic camera system (30) which has a plurality of sensor regions (33) for detecting light beams incident from different directions; ii) capturing (82) an image (35) of the component (45) by means of the plenoptic camera system (30); iii) determining (83) a suitability of the component (45) for use in the turbomachine (1) based on the captured image (35).
G01N 21/88 - Investigating the presence of flaws, defects or contamination
G01N 21/954 - Inspecting the inner surface of hollow bodies, e.g. bores
F01D 11/12 - Preventing or minimising internal leakage of working fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible, deformable or resiliently biased part
F04D 29/52 - CasingsConnections for working fluid for axial pumps
G01N 21/956 - Inspecting patterns on the surface of objects
13.
MASKING MEANS FOR COVERING A THERMAL SPRAY LAYER ON A COMPONENT OF A FLUID MACHINE, AND METHOD FOR PROCESSING A COMPONENT OF A FLUID MACHINE
The invention relates to a masking means (14) for covering a surface region (12) of a component (10) of a fluid machine, in particular for covering a thermal spray layer, wherein the masking means (14) comprises at least one crosslinkable elastomer pre-product with a dynamic viscosity ranging between 21000 mPas and 39000 mPas at a temperature of 25±0.2°C. The invention also relates to a method for processing a component (10) of a fluid machine in which at least one surface region (12) of the component (10) is first covered by such a masking means (14) and the component (10) is then processed.
The invention relates to an air humidifier (1) having a mixing chamber (5) in which is disposed an atomizing nozzle (9) configured to discharge a liquid (25) as a spray mist (10). The mixing chamber (5) is configured such that a gas (26) conveyed along a main flow path (8) through the mixing chamber (5) is mixed with the spray mist (10) and discharged at an outlet opening (7) of the mixing chamber (5). The atomizing nozzle (9) has a swirl device configured to impart a swirl to droplets (11) of the spray mist (10) in order to emit the spray mist (10) as a straight circular spray cone (12). It is provided that the mixing chamber (5) has a separating device (16) configured to catch droplets (11) of the circular spray cone (12) that move from the atomizing nozzle (9) along a hollow cone (14) having a predetermined interior angle (15), and to supply droplets (11) that move inside the hollow cone (14) to the outlet opening (7) of the mixing chamber (5).
B01F 25/313 - Injector mixers in conduits or tubes through which the main component flows wherein additional components are introduced in the centre of the conduit
B01F 23/213 - Mixing gases with liquids by introducing liquids into gaseous media by spraying or atomising of the liquids
B01F 25/10 - Mixing by creating a vortex flow, e.g. by tangential introduction of flow components
B01F 35/00 - Accessories for mixersAuxiliary operations or auxiliary devicesParts or details of general application
B01F 35/221 - Control or regulation of operational parameters, e.g. level of material in the mixer, temperature or pressure
B01F 101/55 - Mixing liquid air humidifiers with air
H01M 8/04119 - Arrangements for control of reactant parameters, e.g. pressure or concentration of gaseous reactants with simultaneous supply or evacuation of electrolyteHumidifying or dehumidifying
15.
METHOD FOR IMAGING A SURFACE OF A TURBOMACHINE AND DETECTING DAMAGE
The present invention relates to a method for imaging a surface in an internal space of an axial turbomachine, wherein the surface is captured in a sequence using an imaging device, i.e.—only a portion is captured with the imaging device at a respective time, thus generating only a partial image of the surface; the imaging device and the surface are moved relative to each other such that different portions of the surface are captured over the course of time, thus generating different partial images, and wherein the partial images are stitched together to produce an image of the surface.
The invention relates to a rotor shaft for an electric motor, in particular for an aircraft engine, wherein the rotor shaft has a forged attachment flange, wherein the attachment flange is provided for attachment to another shaft in order to transmit a force and/or a torque, comprises a first axial end facing the other shaft, and comprises a base plate on a second axial end opposite the first axial end. It is provided that the rotor shaft has a coolant distribution body that is additively manufactured at least in some regions, wherein the additively manufactured coolant distribution body is arranged on the base plate of the forged attachment flange in a radially centered manner, and the rotor shaft has a rotor device, which radially surrounds the additively manufactured coolant distribution body and is joined to the base plate of the forged attachment flange at least in a force-fitting manner.
H02K 9/19 - Arrangements for cooling or ventilating for machines with closed casing and closed-circuit cooling using a liquid cooling medium, e.g. oil
B64D 33/08 - Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of power plant cooling systems
H02K 7/00 - Arrangements for handling mechanical energy structurally associated with dynamo-electric machines, e.g. structural association with mechanical driving motors or auxiliary dynamo-electric machines
17.
STATOR DEVICE FOR DISPOSITION WITHIN A GIVEN TURBINE CASING OF A TURBOMACHINE, CONNECTION SYSTEM FOR A TURBMACHINE, AND TURBOMACHINE
A stator device for disposition within a given turbine casing of a turbomachine, the stator device being provided on its radially outer side with an axially forward connecting element having a radially inward facing forward connecting surface for connection to a forward receiving surface of the turbine casing and an axially rearward connecting element having a radially outward facing rearward connecting surface for connection to a rearward receiving surface of the turbine casing, the rearward connecting surface being pre-curved in the circumferential direction eccentrically with respect to the rearward receiving surface; the rearward connecting element having a rearward rib portion extending substantially linearly away from a platform of the stator device and providing the rearward connecting surface at its radially outer end; and the rib portion being provided at its radially outer end with axially extending projections distributed along the circumferential direction for radially retaining the stator device to the turbine casing.
A method for creating a computer-implemented data system, includes: providing a virtual 3D engine model of an engine including a plurality of components; providing component-specific data associated with said each of the plurality of components; and virtually linking the virtual 3D engine model to the component-specific data by creating virtual data markers in the virtual 3D engine model at a coordinate of each of the plurality of components, and associating each virtual data marker with the component-specific data of its corresponding one of the plurality of components. In this regard, the component specific data may include, for example, part number, name, inspection intervals, etc. The engine may be an aircraft engine, and may further be an aircraft engine casing. Further, in addition to the virtual 3D engine model, the method may include providing 2D images of the plurality components, and the step of virtually linking may further include linking the 2D images to the component specific data.
The present invention relates to a module for a turbomachine, with a guide vane arrangement, a seal carrier, which is arranged radially inside an inner platform of the guide vane arrangement, seal carrier walls, namely, a first seal carrier wall and a second seal carrier wall, and a sliding member as well as a connecting element, wherein the first seal carrier wall and the seal carrier are formed in a one-piece manner with each other, and wherein the seal carrier walls are multipiece in construction relative to each other, and the second seal carrier wall is fastened to the first seal carrier wall and the seal carrier by way of the connecting element, wherein the sliding member holds the seal carrier walls spaced apart from each other in such a manner that they bound axially an intervening space with each other.
The invention relates to a spring device (20) with a first suspension element (21), a second suspension element (22), and a plurality of constant-force-spring elements (1), wherein the first and second suspension element (21, 22) are suspended in a movable manner relative to each other in a spring direction (25) via the constant-force-spring elements (1), and at least some of the constant-force-spring elements (1) are arranged in a packet (31-34) in a translationally symmetrical manner relative to one another in a translation direction (35), which has at least one component (35.1) in the spring direction (25), and/or are arranged in a rotationally symmetrical manner relative to one another about a rotational axis (40, 50), which lies at least partly parallel to the spring direction (25), when viewed in the spring direction (25).
F16F 1/02 - Springs made of steel or other material having low internal frictionWound, torsion, leaf, cup, ring or the like springs, the material of the spring not being relevant
F16F 3/02 - Spring units consisting of several springs, e.g. for obtaining a desired spring characteristic with springs made of steel or of other material having low internal friction
09 - Scientific and electric apparatus and instruments
35 - Advertising and business services
37 - Construction and mining; installation and repair services
42 - Scientific, technological and industrial services, research and design
Goods & Services
Generators for aircraft, compressors; machine coupling and
transmission and propulsion components (other than for land
vehicles); systems using propulsive and non-propulsive power
(machines) for aircraft and component parts thereof included
in this class, including turbines, motors, engines,
thrusters, nacelles, thrust reversers; auxiliary power units
for air vehicles (machines); lubrication systems for motors,
engines and turbines of air vehicles (machines); test
benches for motors, engines, turbines and other thrusters
(machines) for aircraft. Electric and electronic apparatus and instruments namely
generators and/or starters for fixed or mobile installations
for aircraft; electric, electronic and magnetic pressure,
speed, displacement, temperature, position and vibration
sensors; electronic on-board or ground systems, apparatus
and equipment for data and parameter acquisition and
processing; electric and electronic maintenance and control
equipment and hardware for generators, starters and
integrated sets for generating propulsive and non-propulsive
power. Sales services for propulsion and non-propulsion power
systems (machines) for aircraft; administrative and
commercial management of parts, replacement equipment for
users of engines, systems, equipment and parts of aircraft;
commercial advice on propulsion systems for airplanes,
turbines; processing services for acquisition of data
recorded during the operation of aircraft engines, systems,
equipment and parts [office work]. Repair, overhaul, servicing and maintenance services for
propulsive and non-propulsive power systems (machines) for
aircraft and their component parts, including turbines,
engines, thrusters, nacelles, thrust reversers; advisory
services for definition and selection of tools for repair,
overhaul, servicing, standardization and maintenance of
aircraft systems, equipment and parts. Technical, scientific and industrial research; engineering;
research and development (engineering work) in the
aeronautical field; analysis of technical data; services
provided by engineers relating to evaluations, estimates and
research in connection with the technologies used in
systems, equipment and parts of aeronautical vehicles;
testing of machines and materials; design and development of
software and computer programming; analysis and expertise
services for aircraft equipment and parts; analysis and
expertise of data recorded during the operation of aircraft
engines, systems, equipment and parts; technical project
studies in connection with aeronautical vehicles and their
components, including motors and engines, aircraft engine
pods, reactors, thruster units or reversers, aeronautical
vehicles.
The present invention relates to a method for testing a material for producing a component for a turbomachine, in particular an aircraft engine, comprising the following steps: i) providing the material in powder form; ii) sequentially measuring in each case a portion of the pulverulent material using a hyperspectral camera system; iii) determining the suitability of the pulverulent material for the production of the component based on the measurement results ascertained in step ii).
G01N 21/31 - Investigating relative effect of material at wavelengths characteristic of specific elements or molecules, e.g. atomic absorption spectrometry
G01N 21/85 - Investigating moving fluids or granular solids
G01N 21/84 - Systems specially adapted for particular applications
23.
METHOD FOR RECOGNIZING AN ANOMALY IN MEASURED OPERATING VALUES OF A TURBOMACHINE, AND ANALYSIS DEVICE AND MACHINE MONITORING DEVICE
A method for recognizing an anomaly in measured operating values of a turbomachine, in particular an aircraft turbine, including repeatedly detecting measured operating values of particular operating parameters of a turbomachine uring an operating period of the turbomachine, using sensors of the turbomachine, ascertaining quasi-steady-state time intervals of the operating period, using an analysis device, generating quasi-steady-state operating data points for the quasi-steady-state time intervals, the quasi-steady-state operating data points including averaged measured operating values, ascertaining particular expected data points which include particular expected operating values of the particular operating parameters, ascertaining particular measured operating value residuals of the particular operating parameters, checking the measured operating value residuals of the particular quasi-steady-state operating data points for compliance with predetermined anomaly criteria with regard to predefined nominal values of the measured operating value residuals, and transferring an anomaly indicator, which includes a violated anomaly criterion of the anomaly criteria and a point in time of the violation, to a machine monitoring device.
The present invention relates to a method for introducing a recess (3) into a workpiece (1), wherein the recess (3) is introduced with a processing cathode (2) by electrochemical ablation, wherein a flank (1.3) delimiting the recess (3) is exposed with the ablation, which flank extends from a first surface (1.1) of the workpiece (1) in the direction of an opposite second surface (1.2) of the workpiece (1), wherein a protective anode (7.1, 7.2) is arranged on at least one of the surfaces (1.1, 1.2) during removal, which protective anode is associated with the flank (1.3) and bears against the at least one surface (1.1, 1.2) in electrical contact with the workpiece (1), and wherein the protective anode (7.1, 7.2) is offset outwards relative to the flank (1.3), i.e. away from the recess (3).
METHOD FOR MACHINING A ROTOR OF AN AIRCRAFT ENGINE, WHICH HAS BLADES THAT ARE PROVIDED WITH A COATING AT LEAST IN THE REGION OF THEIR BLADE TIPS, AND CUTTING TOOL INCLUDING CUTTING WIRE
The invention relates to a method for machining a rotor (10) of an aircraft engine, which has blades (32) that are provided with a coating (34) at least in the region of their blade tips (38). The method comprises the steps: a) cutting the coating (34) along a first blade tip edge (36a) of a blade (32) of the rotor (10) by means of a cutting tool (40); b) cutting the coating (34) along a second blade tip edge (36b) of the blade (32) of the rotor (10) by means of the cutting tool (40); and c) cutting the coating (34) along the blade tip (38) of the blade (32) of the rotor (10) by means of the cutting tool (40). The invention further relates to a cutting tool (40) including cutting wire (44) for use in such a method.
B26F 3/12 - Severing by using heat with heated members with heated wires
B23P 15/04 - Making specific metal objects by operations not covered by a single other subclass or a group in this subclass turbine or like blades from several pieces
26.
METHOD FOR SMOOTHING AT LEAST ONE SURFACE REGION OF A DUCT OF AN ADDITIVELY MANUFACTURED COMPONENT OF AN AIRCRAFT ENGINE
The invention relates to a method for smoothing at least one surface region of a duct (12) of an additively manufactured component (10) of an aircraft engine, in which at least one chemical removal agent (20) is passed through the duct (12) and removes a material of the component (10) until a predetermined surface quality is achieved at least in the surface region to be smoothed. The chemical removal agent (20) comprises at least ammonium bifluoride.
B22F 5/10 - Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product of articles with cavities or holes, not otherwise provided for in the preceding subgroups
B22F 10/38 - Process control to achieve specific product aspects, e.g. surface smoothness, density, porosity or hollow structures
B22F 5/00 - Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product
B22F 5/04 - Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product of turbine blades
The invention relates to an aircraft propulsion system (10), comprising a nacelle (20) that forms a flow channel (221) through which a flow (21) can flow and in which a propulsion machine (45) is disposed, wherein at least one surface (31, 32) of the nacelle (20) can be used as a heat sink for a cooling device (30).
The invention relates to an aircraft drive (10), comprising a first nacelle (20) through which a first flow (21) can flow and in which a drive engine (45) is arranged, and at least one second nacelle (30) arranged on the first nacelle (20) and through which a second flow (31) can flow and in which a cooling device (55) is arranged.
F02C 7/14 - Cooling of plants of fluids in the plant
F02K 3/077 - 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 the plant including ducted fans, i.e. fans with high volume, low-pressure outputs, for augmenting jet thrust, e.g. of double-flow type the plant being of the multiple flow type, i.e. having three or more flows
F02K 3/115 - Heating the by-pass flow by means of indirect heat exchange
29.
FUEL SYSTEM FOR SUPPLYING AN AIRCRAFT WITH HYDROGEN, METHOD AND AIRCRAFT
The invention relates to a fuel system (1) for supplying an aircraft (2) with hydrogen (3). The fuel system (1) comprises a first inner tank (4) and a separate second inner tank (6), each for storing hydrogen (3), and an outer tank (5) which surrounds the inner tanks (4, 6). The first inner tank (4) and the second inner tank (6) are fluidically connected, separately from one another, to at least one first supply device (7) for supplying the aircraft (2) with hydrogen (3). The invention also relates to an aircraft (2) having a fuel system (1), and to a method.
The invention relates to a jet ejector pump (10) for a recirculation system (1) of a fuel cell system in a fuel cell drive (1a), in particular a fuel cell drive (1a) in the form of an aircraft engine, for moistening and circulating hydrogen in the fuel cell system, having at least one fuel cell (2), comprising a water separator (20) for separating water and forming drop-free gas from a moist exhaust gas of the fuel cell (2), and a gas delivery device (30) which is arranged downstream of, in particular adjacent to, the water separator (20), wherein the water separator (20) has a suction connection (22) for feeding the exhaust gas into the water separator (20), wherein the water separator (20) has a water outflow (25) for removing water separated from the moist exhaust gas, wherein the water separator (20) has a drop-free gas connection (27) which leads into the gas delivery device (30). In order to be better suited to aeronautical applications, it is proposed according to the invention that the water separator (20) is tubular between the suction connection (22) and the gas delivery device (30) and has a curvature about an angle a of at least 60° and at maximum 120°.
H01M 8/04119 - Arrangements for control of reactant parameters, e.g. pressure or concentration of gaseous reactants with simultaneous supply or evacuation of electrolyteHumidifying or dehumidifying
31.
METHOD FOR ELECTROCHEMICALLY MACHINING A WORKPIECE
The invention relates to a method for machining a workpiece by an electrochemical machining process in which material is removed from the workpiece in an electrolyte liquid, where the electrolyte liquid is then filtered in a membrane filter system which has a membrane that undergoes a relative movement in the membrane filter system during the filtering process, and the filtered electrolyte liquid is reused for the electrochemical machining process.
G05B 17/02 - Systems involving the use of models or simulators of said systems electric
B24B 19/26 - Single purpose machines or devices for particular grinding operations not covered by any other main group for grinding workpieces with arcuate surfaces, e.g. parts of car bodies, bumpers or magnetic recording heads
33.
ROTOR ARRANGEMENT FOR A LOW-PRESSURE TURBINE OF A TURBOMACHINE
The invention relates to a rotor arrangement for a low-pressure turbine of a turbomachine with end-side linkage to a shaft of the turbomachine, comprising a plurality of rotating stages, which are arranged in a flow direction and are connected to one another, wherein the last rotating stage in the flow direction can be linked to the shaft by a rotor disk.
The invention relates to a housing structure for a turbomachine, with a housing shell and at least one containment ring arranged in therein, wherein the housing structure surrounds a flow channel in a ring-shaped manner, in which at least one rotating stage with a guide vane arrangement and a rotating blade arrangement is arranged, as well as a turbomachine having such a housing structure.
The invention relates to a turbomachine for a flight propulsion drive with a compressor, a combustion chamber, a turbine through which a gas flow flows in the flow direction of turbomachine, and a heat exchanger downstream of the turbine, wherein the heat exchanger is equipped to generate steam from water using energy from the gas flow, which can be supplied with fuel to the gas flow for combustion in the combustion chamber.
The invention relates to a turbomachine for a flight propulsion drive with a compressor, a combustion chamber, a turbine through which a gas flow flows in a flow direction of the turbomachine, and a heat exchanger downstream of the turbine, wherein the heat exchanger is equipped to generate steam from water using energy from the gas flow, which can be supplied with the fuel to the gas flow for combustion in the combustion chamber.
The present invention relates to a control device for a fuel cell system, in particular a fuel cell system of a drive system of an aircraft, which has at least one fuel cell, an air supply line with an air supply device for controlling an air mass flow which is supplied to the fuel cell, and an air humidification device for humidifying the air in the air supply line, characterised by an air humidity detection device for detecting or estimating an air humidity, a first control loop for controlling the air mass flow as a function of the detected or estimated air humidity, and a second control loop for controlling a humidification parameter of the air humidification device as a function of the detected or estimated air humidity and/or the air mass flow.
H01M 8/04119 - Arrangements for control of reactant parameters, e.g. pressure or concentration of gaseous reactants with simultaneous supply or evacuation of electrolyteHumidifying or dehumidifying
An aircraft having a fuel cell (20) and an air supply device (30) for supplying air for operating the fuel cell (20) and for cooling a heat exchanger (21) connected to the fuel cell (20), the aircraft (1) having at least one air duct (10) whose cross section widens in the direction of flow (5) of the air downstream of an air inlet opening (11) in at least one region (35) of the peripheral surface. Also provided is a method for operating such a fuel cell (20) of an aircraft (1) with an air supply device (30) for operating the fuel cell (20) and for cooling a heat exchanger (21) connected to the fuel cell (20).
B64D 27/24 - Aircraft characterised by the type or position of power plants using steam or spring force
B64D 41/00 - Power installations for auxiliary purposes
H01M 8/0265 - CollectorsSeparators, e.g. bipolar separatorsInterconnectors characterised by the configuration of channels, e.g. by the flow field of the reactant or coolant the reactant or coolant channels having varying cross sections
H01M 8/04007 - Auxiliary arrangements, e.g. for control of pressure or for circulation of fluids related to heat exchange
H01M 8/04111 - Arrangements for control of reactant parameters, e.g. pressure or concentration of gaseous reactants using a compressor turbine assembly
40.
METHOD FOR MATERIAL-REMOVING MACHINING OF A COMPONENT FOR A TURBOMACHINE
The present invention is directed to a method for the material-removing machining of a component for a turbomachine that includes the steps of i) recording a distance image by contact-free measurement of at least one surface of the component that is to be machined; ii) comparing the distance image to a computer model of the component and determining the sites of the component that are to be machined based on deviations between the distance image and the computer model; iii) generating a tool path for the sites of the component that are to be machined; and iv) material-removing machining of the component on the basis of the tool path by spark erosion, laser drilling, or conventional drilling.
G05B 19/401 - Numerical control [NC], i.e. automatically operating machines, in particular machine tools, e.g. in a manufacturing environment, so as to execute positioning, movement or co-ordinated operations by means of programme data in numerical form characterised by control arrangements for measuring, e.g. calibration and initialisation, measuring workpiece for machining purposes
41.
METHOD FOR PRODUCING AN OXIDATION PROTECTION COATING AT LEAST IN REGIONS ON A COMPONENT OF A THERMAL GAS TURBINE
The invention relates to a method for producing at least in regions an oxidation protection coating on a component of a thermal gas turbine. In accordance with the invention, the method comprises the steps of coating the component at least in regions with a lacquer, which comprises at least one UV-curable binder and metal particles, curing the lacquer by exposure to UV light, and thermal treatment of the component at least in the region of the cured lacquer for production of the oxidation protection coating.
C21D 1/72 - Temporary coatings or embedding materials applied before or during heat treatment during chemical change of surfaces
B05D 3/04 - Pretreatment of surfaces to which liquids or other fluent materials are to be appliedAfter-treatment of applied coatings, e.g. intermediate treating of an applied coating preparatory to subsequent applications of liquids or other fluent materials by exposure to gases
B05D 3/06 - Pretreatment of surfaces to which liquids or other fluent materials are to be appliedAfter-treatment of applied coatings, e.g. intermediate treating of an applied coating preparatory to subsequent applications of liquids or other fluent materials by exposure to radiation
B05D 7/16 - Processes, other than flocking, specially adapted for applying liquids or other fluent materials to particular surfaces or for applying particular liquids or other fluent materials to metal, e.g. car bodies using synthetic lacquers or varnishes
A description is given of a fuel cell comprising an electrode-membrane unit comprising a cathode and an anode, a cathodal gas diffusion element, an anodal gas diffusion element, the electrode-membrane unit being accommodated between the gas diffusion elements; a cathodal bipolar plate, and an anodal bipolar plate. Provision is made here for the cathodal gas diffusion element or/and the anodal gas diffusion element to have at least one structural element facing the respective bipolar plate and integrally bonded to the relevant gas diffusion element.
A computer-implemented method for simulating particle impacts in a gas path of an aircraft engine, the method including i) providing a structural-mechanical model of at least one section of the gas path, the model including structurally or mechanically modeled airfoils, ii) placing a particle at a position in the gas path of the model, iii) moving the particle with a velocity vector that was previously determined in a computational fluid dynamics (CFD) simulation in a CFD model of the at least one section of the gas path for a fluid flowing through the gas path, and iv) detecting an impact when the moving particle hits a component of the structural-mechanical model.
A rotor disk for a blade ring of an aircraft engine, in particular for a turbine stage thereof, including an attachment section for attachment to a shaft for torque transfer, a main section that extends radially inwardly from a blade root receptacle in the radial direction, a connecting section that connects the attachment section and the main section, and a plurality of through openings, situated in the circumferential direction, at a radially inner end of the connecting section. A rotor disk whose stresses are reduced in the event of load is provided in that the connecting section has an undercut. An apex of the undercut is radially situated above the through opening in the range of 5%-50% of the axial length of a through opening, and/or is axially spaced apart from an axial end of the through opening at 5%-35% of the axial length of the through opening.
The invention relates to a tool (1) for machining a component (30) via electrochemical material removal, comprising a machining cathode (2) with a front side (2.1) for brniging towards a surface (30.1) of the component (30) to be machined, and comprising a protective electrode layer (20) arranged on a rear side (2.2) of the machining cathode (2) opposite the front side (2.1), with the protective electrode layer (20) being electrically insulated from the machining cathode (2).
The invention relates to a damping device (20) for an apparatus (10) for turning components (30), wherein the damping device (20) can be arranged on a rotatable holder (11) for clamping the component (30) of the apparatus (10), wherein the damping device (20) has at least one support element (21) that is movably mounted on said holder.
The invention relates to an adjustment system for a compressor in a gas turbine, in particular in an aircraft gas turbine, for the adjustment of adjustable guide vanes, including an actuator device with a first actuator for the adjustment of the guide vanes and an adjusting device with a first adjusting valve for the hydraulic operation of the first actuator, wherein the adjusting device can adjust and lock in position the first actuator by way of the hydraulic operation, is characterized in that the actuator device is assigned a locking device for additional fixation and can be fixed in a position by the locking device.
The invention relates to a device for machining a component (2) by means of electrochemical material removal, comprising a component holder (3) for arranging the component (2), and a first machining station (10), wherein the first machining station (10) and the component holder (3) are mounted such that they can rotate relative to one another about a component axis (4) passing through the component holder, and wherein the first machining station (10) has a first axis module (11) and a first tool carrier (12), wherein a first machining electrode (14) is arranged on the first tool carrier, and wherein the first tool carrier (12) is mounted on the first axis module such that it can rotate about a first tool axis (13).
A drive system (10) including a gas turbine (1), designed in particular as an aircraft engine. The gas turbine (1) includes a core flow channel (1c) in which at least one compressor (2), in particular a mixing chamber (3a), a combustion chamber (3), and a turbine (4), are situated in the flow direction, and a steam system (20) for separating water from an exhaust gas stream of the core flow channel (1c), for generating steam, and for conveying the steam, in particular across the mixing chamber (3a) into the combustion chamber (3). A drive system (10) whose efficiency is increased is provided in that the steam system (20) is coupled to a separate cooling system (30) in order to contribute to the separation of the water for generating the steam from an exhaust gas stream of the core flow channel (1c), via absorption and discharge of heat.
F02C 3/34 - Gas-turbine plants characterised by the use of combustion products as the working fluid with recycling of part of the working fluid, i.e. semi-closed cycles with combustion products in the closed part of the cycle
F02C 7/141 - Cooling of plants of fluids in the plant of working fluid
The present invention relates to a bipolar plate (4) for a fuel cell (6), with a first reaction-gas channel structure (11) for carrying a first reaction gas, and with a coolant channel (15) for carrying a coolant (55), wherein the first reaction-gas channel structure (11) has a first inlet (11a) for feeding in the first reaction gas and a first outlet (11b) for discharging the first reaction gas, and wherein, with respect to a first straight connecting line (31) drawn between the first inlet (11a) and the first outlet (11b), the coolant channel (15) extends in such a way that it crosses the first straight connecting line (31) at least twice.
H01M 8/0258 - CollectorsSeparators, e.g. bipolar separatorsInterconnectors characterised by the configuration of channels, e.g. by the flow field of the reactant or coolant
H01M 8/0263 - CollectorsSeparators, e.g. bipolar separatorsInterconnectors characterised by the configuration of channels, e.g. by the flow field of the reactant or coolant having meandering or serpentine paths
H01M 8/0267 - CollectorsSeparators, e.g. bipolar separatorsInterconnectors having heating or cooling means, e.g. heaters or coolant flow channels
51.
METHOD FOR SUPPLYING AN AIR BEARING OF A FLIGHT PROPULSION SYSTEM BY MEANS OF A FUEL CELL SYSTEM, AND FLIGHT PROPULSION SYSTEM
A supply device (10) and to a method (100) for supplying an air bearing (11) via a fuel cell system (12) having at least one anode (14) and at least one cathode (15) as well as a process gas device (17) for supplying the anode (14) and the cathode (15) with fuel and ambient air and for discharging spent process gases.
H01M 8/04111 - Arrangements for control of reactant parameters, e.g. pressure or concentration of gaseous reactants using a compressor turbine assembly
B64D 27/02 - Aircraft characterised by the type or position of power plants
B64D 41/00 - Power installations for auxiliary purposes
H01M 8/04089 - Arrangements for control of reactant parameters, e.g. pressure or concentration of gaseous reactants
The invention relates to a device (1) for machining a component (2) via electrochemical material removal, comprising a component holder (3) for arranging the component (2), a plurality of machining stations (10.1 - 10.4) for machining the component (2) via electrochemical material removal, and a positioning unit (30) with which the machining stations (10.1 - 10.4) and the component holder can be shifted relative to one another, wherein at least two of the machining stations (10.1 - 10.4) are constructed differently.
A component classification device for classifying components into predefined component classes, including a camera device that is configured to generate image data of a component to be classified, and a weighing device that is configured to generate weight data of the component to be classified. The component classification device includes an evaluation device that is configured to generate predefined image features from the image data according to a predefined image feature extraction method, and to supply the image data to a pretrained first neural network, and to generate bottleneck features of the image data from a predefined bottleneck layer of the first neural network. The component classification device includes a classification unit that is configured to assign at least one of multiple predetermined component classes, which describe predetermined component groups and/or components, to the component according to a predetermined classification method, based on the weight data, the image features, and the bottleneck features.
G06V 10/40 - Extraction of image or video features
G06V 10/764 - Arrangements for image or video recognition or understanding using pattern recognition or machine learning using classification, e.g. of video objects
G06V 10/77 - Processing image or video features in feature spacesArrangements for image or video recognition or understanding using pattern recognition or machine learning using data integration or data reduction, e.g. principal component analysis [PCA] or independent component analysis [ICA] or self-organising maps [SOM]Blind source separation
G06V 10/82 - Arrangements for image or video recognition or understanding using pattern recognition or machine learning using neural networks
A blisk has at least one blade, with a blade airfoil and a blade root; a platform, the blade being integrally attached to the platform; and a fillet arranged on the blade root and between the blade airfoil and the platform. The fillet merges into the blade at a blade connection. The fillet merges into the platform at a platform connection. The fillet extends with a longitudinal extent around the blade root and a transverse extent from the platform to the blade airfoil. The fillet has a variable radius along the transverse extent. The variable radius has, at least in a first section of the fillet, a minimum radius which, at least in the first section, is spaced apart from the platform by at least 15% of the transverse extent along the transverse extent of the fillet.
A method classifies a component feature of a component, the component including a blisk or a part of a blisk for a turbomachine, which has been manufactured using a production process. The method includes classifying the component feature as a function of a first feature specification and a second feature specification for a measured variable of the component feature. A second tolerance range of the second feature specification is extended as compared to a first tolerance range of the first feature specification. A second region of applicability of the component for the second feature specification is smaller than a first region of applicability of the component for the first feature specification. The production process reproducibly and/or systematically causes a larger mean deviation of the measured variable in the second region of applicability than in the first region of applicability.
A damper ring (1) for reducing unwanted vibrations of a blisk (2), which damper ring (1) is disposable at the radially inner side of a blade ring (3) of the blisk (2). The damper ring (1) features at least one damper element (4) configured to dissipate vibrational energy of the blisk (2) and/or to transfer vibrational modes of the blisk into vibrational modes different from the vibrational modes of the blisk. The invention also relates to a blisk (2) and to a turbomachine (13).
A brush seal for a turbomachine which has improved sealing performance above an operating temperature of 700° C. The brush seal includes a bristle package made of a Ni-based alloy. A turbomachine and to a method for manufacturing a brush seal is provided.
The invention is a method for operating a turbomachine for a flight propulsion drive having a compressor through which a gas stream flows in a flow direction, a combustion chamber, a turbine, and a heat exchange device situated downstream of the turbine, wherein the heat exchange device extracts water from the gas stream and the water is supplied in the combustion chamber for the combustion of fuel.
A turbofan engine with a low-pressure turbine module having no more than four stages and a fan coupled to the low-pressure turbine module via a gearbox, the turbofan engine having a maximum thrust of at least 70 kN and at most 300 kN, and the low-pressure turbine module (4.2) having a ratio of the exit annulus area to the inlet annulus area, Aout/Ain, of at least 2.2 and at most 3.3.
The present invention is directed to a method for operating a flight-propulsion system of an aircraft, the flight-propulsion system having a propulsion unit, a water discharger arranged downstream of the propulsion unit and a reservoir for receiving water, in which method the propulsion unit is operated and, during a flight of the aircraft, water resulting from the operation of the propulsion unit is discharged by the water discharger, wherein at least some of the discharged water is fed to the reservoir, and wherein at least some of the water that is fed to the reservoir is given off to the surroundings while the flight is still in progress, that is to say is only temporarily stored in the reservoir.
The present invention relates to a device (1) for machining a component (2) by means of electrochemical machining, the device comprising a machining cathode (11) for electrochemically removing material from the component (2), a component holder (6) for holding the component (2) during the machining, and a positioning unit (12) for moving the machining cathode (11) relative to the component holder (6). The component holder (6) and the positioning unit (12) are movable relative to each other in a penetration direction (19) of the machining cathode (11), the machining cathode (11) is additionally laterally movable by means of the positioning unit (12), i.e. at an angle to the penetration direction (19), and the positioning device (12) has a linear drive (13) by means of which the lateral movability is implemented.
The present invention relates to a method for measuring a component of a fluid machine with respect to material changes, according to which the component is excited by means of a vibration exciter, and, in order to determine inherent values of the component, a respective vibration deflection of the component is measured at multiple points of the component by means of a vibration sensor.
opt_1opt_2opt_1opt_2opt_1opt_2opt_2, a recirculation circuit (19) being associated with the first heat source (11) in the cooling circuit (14), by means of which recirculation circuit any cooling fluid (16) already utilised in operation for cooling the first heat source (11) can be used again for cooling the first heat source (11) before passing through the heat exchanger (13), the heat exchanger (13) also having an actuatable inlet (13.1).
The invention relates to an aircraft (1) having a fuel-cell propulsion system (2), wherein the fuel-cell propulsion system (2) comprises - a fuel cell (3) for supplying electricity to an electric propulsion apparatus (4) of the aircraft (1), - a fuel store (5) for storing fuel for the fuel cell (3), and - a cooling apparatus (6) for cooling the fuel cell (3), wherein - a main heat exchanger (7) of the cooling apparatus (6) and the fuel store (5) are arranged on a top side (8) of a fuselage (9) of the aircraft (1), and - the main heat exchanger (7) is arranged in front of the fuel store (5) toward the aircraft nose.
B60L 50/70 - Electric propulsion with power supplied within the vehicle using propulsion power supplied by batteries or fuel cells using power supplied by fuel cells
B64C 1/00 - FuselagesConstructional features common to fuselages, wings, stabilising surfaces or the like
B64D 27/00 - Arrangement or mounting of power plants in aircraftAircraft characterised by the type or position of power plants
B64D 37/04 - Arrangement thereof in or on aircraft
H01M 8/04007 - Auxiliary arrangements, e.g. for control of pressure or for circulation of fluids related to heat exchange
H01M 8/04082 - Arrangements for control of reactant parameters, e.g. pressure or concentration
65.
METHOD AND ELECTRODE FOR MACHINING COMPONENTS BY ELECTROCHEMICAL MACHINING
The invention relates to a method for the electromechanical machining of a component with at least one electrode which has a first working face with an outer contour which is shaped so as to form a gap complementary to a surface, to be produced by the electrochemical machining, of the component and which has a second working face which is able to be arranged at an edge of the produced surface of the component. In the method, first of all the component is provided, and the first working face of the electrode is positioned in a first machining position with respect to the component. Then, the component is machined with the first working face in order to produce the surface, before the machining of the component with the first working face is ended at a predetermined position. Subsequently, the component is machined with the second working face of the electrode.
The invention relates to an aircraft fuel cell propulsion unit (10) with a fuel cell system (12), having a compressor (14) which is configured, depending on the environmental conditions of the aircraft fuel cell propulsion unit (10), to compress air (L) for supplying the fuel cell system (12) in the region of an optimum operating point in each case.
The invention is directed to a method for cleaning a component from powder residues of an additive layering method using a cleaning device, wherein a machine plate and the component arranged thereon are excited during a cleaning process by a vibration actuator of the cleaning device with a set resonance frequency of the machine plate to carry out a mechanical vibration. It is provided that the machine plate is excited by predefined vibration movements of the at least one vibration actuator to the predefined mechanical vibration, wherein the predefined vibration movements of the at least one vibration actuator occur in parallel to a main plane of the machine plate. The invention also relates to a cleaning device for cleaning an at least partially additively manufactured component, in particular a component of a turbomachine.
B08B 7/02 - Cleaning by methods not provided for in a single other subclass or a single group in this subclass by distortion, beating, or vibration of the surface to be cleaned
B08B 13/00 - Accessories or details of general applicability for machines or apparatus for cleaning
The present invention relates to a method of calibrating a thermal FEM-model of a turbomachine, the method comprising: i) creating a meta-model of the thermal FEM-model; ii) feeding, for a set of thermal variables, a set of input values to the meta-model for a calculation in the meta-model; iii) obtaining a set of output values from the calculation in the meta-model for the set of input values; iv) comparing the set of output values to measurement data of the turbomachine.
A module for a turbomachine, including a guide blade arrangement, a seal carrier that is situated radially within an inner platform of the guide blade arrangement, seal carrier walls, namely, a first seal carrier wall and a second seal carrier wall, and a sliding body as well as a connecting element. The seal carrier walls have a multipart design with respect to one another, and the second seal carrier wall is fastened to the first seal carrier wall and to the seal carrier via the connecting element. The sliding body holds the seal carrier walls at a distance from one another in such a way that they mutually axially delimit a clearance in which the guide blade arrangement engages via a radially inwardly extending guide pin. A radially inner section of the second seal carrier wall has frictional contact relative to the seal carrier.
01 - Chemical and biological materials for industrial, scientific and agricultural use
06 - Common metals and ores; objects made of metal
07 - Machines and machine tools
38 - Telecommunications services
40 - Treatment of materials; recycling, air and water treatment,
09 - Scientific and electric apparatus and instruments
11 - Environmental control apparatus
37 - Construction and mining; installation and repair services
39 - Transport, packaging, storage and travel services
42 - Scientific, technological and industrial services, research and design
Goods & Services
Separator membranes for hydrogen fuel cells, namely, polymeric membranes in chemical form for the separation of gas Hydrogen storage systems consisting of metal containers for storing gases Generators of electricity and emergency electricity, in particular for aircraft; Fuel cell energy converters, namely, portable electric power generators; portable electric power generators based on integrated fuel cell hybrid energy converters; Parts of machines, namely, Heat exchangers and conduits for fluid and heat transfer for integrated fuel cell power generation systems and subsystems in the nature of gas operated power generators; Integrated hydrogen-fuel systems comprised of heat exchangers being parts of aircraft engines, containers, valves as machine components, pumps for cooling engines and lines, namely, parts of machines, for propulsion systems for aircraft in the nature of aircraft engines; Hydrogen dispensing pumps for service filling stations; Parts for electrolysis machines for generating hydrogen, namely, separators and membranes for generators in the nature of electrolysis apparatus for generating hydrogen, circulation frames for generators, baffle plates and containers for generators, rectifier droplet separators for generators, and gas-liquid separators; Parts of machines, namely, Gas lines for discharging gas mixtures, hydrogen and water from drives for aircrafts in the nature of automated hydro-thrust cleaning units for pipelines; air filters for fuel cell systems Electronic transmission of data for use in regulating the fuel system and the fuel cell system and distributing the relevant data to the aircraft, a ground station or an internal memory Power generation; Power generation services; Custom manufacture, for others, of industrial and commercial hydrogen fuel and propulsion systems; Custom manufacture, for others, of fuel cell systems and hydrogen fuel and propulsion systems; Generation of hydrogen; Custom manufacture of fuel cell systems and hydrogen fuel and propulsion systems for others; providing information, advice and consultancy in relation to power generation services Microprocessor-based, control system comprised of microprocessors and downloadable computer software for controlling fuel cell operation; Hydrogen fuel cells; electronic control system, for power generating fuel cell generator modules, comprised of computer hardware with an embedded operating system software, pressure relief valves for power generating, electric switches and electronic circuits; Test stations for fuel cells; Automatic test stations for fuel cells; downloadable computer software for use in operating test stations for fuel cells; downloadable computer software for use in operating automatic test stations for fuel cells; downloadable computer software for use in operating hydrogen test stations; Fuel cells; Fuel cell stacks; Integrated fuel cell systems comprised of fuel cells; Anodes and sensor devices, namely, temperature, humidity and pressure sensors in the nature of hygrometers; cathodes; Fuel cell stacks, heat sensors in the nature of hygrometers, pressure sensors and electronic controls, all for integrated fuel cell power generation systems and subsystems; pressure, heat and temperature sensors in the nature of heat detecting apparatus; computer hardware and downloadable software for controlling the integrated hydrogen fuel system in propulsion systems for aircraft Hydrogen cleaning devices, namely, gas scrubbers; Air filters for fuel cell systems Refueling aircraft with hydrogen; Construction of power generation plants; construction project management and construction supervision in the field of energy generation equipment Physical storage of hydrogen, for example with an integrated fuel system; Distribution of hydrogen and air as fuel for fuel cells; electricity supply through distribution of electricity; Distribution of energy; providing information, advice and consultancy in relation to the distribution and storage of energy Engineering services in the field of the refueling, storage and use of hydrogen as fuel, the conversion of hydrogen to electricity with fuel cells and the installation and integration of such systems, including their control by means of hardware and software; Consultancy in the field of design and development of test stations for fuel cells, fuel cells, integrated hydrogen fuel and propulsion systems, and ancillary equipment; Design of industrial and commercial hydrogen fuel and propulsion systems; Technical advice, research and development and testing services in the field of electricity, propulsion energy from hydrogen and hydrogen-fueled products; Testing services in the field of fuel cells, fuel cell systems, aerospace propulsion systems and hydrogen; Design and testing of hydrogen fuel and propulsion systems and fuel cells, fuel cell systems, aerospace propulsion systems based on fuel cell technologies; Design of alternative energy systems; Technical consultancy, engineering services and project development in the field of hydrogen fuel and drive systems and fuel cells, fuel cell systems, aviation drive systems based on fuel cell technologies; Information, advice and consultancy relating to all of the aforesaid; Technical project management in the field of energy generation engineering services and project development in the field of hydrogen fuel and propulsion systems and fuel cells, fuel cell systems, aviation propulsion systems based on fuel cell technologies; Information, advice and consultancy relating to all of the aforesaid; Technical project management in the field of energy generation engineering services and project development in the field of hydrogen fuel and propulsion systems and fuel cells, fuel cell systems, aviation propulsion systems based on fuel cell technologies; Providing information, advice and consultancy in relation to engineering design services; Technical project management in the field of energy generation
01 - Chemical and biological materials for industrial, scientific and agricultural use
06 - Common metals and ores; objects made of metal
07 - Machines and machine tools
38 - Telecommunications services
40 - Treatment of materials; recycling, air and water treatment,
09 - Scientific and electric apparatus and instruments
11 - Environmental control apparatus
37 - Construction and mining; installation and repair services
39 - Transport, packaging, storage and travel services
42 - Scientific, technological and industrial services, research and design
Goods & Services
Separator membranes for hydrogen fuel cells, namely, polymeric membranes in chemical form for the separation of gas Hydrogen storage systems consisting of metal containers for storing gases Generators of electricity and emergency electricity, in particular for aircraft; Fuel cell energy converters, namely, portable electric power generators; portable electric power generators based on integrated fuel cell hybrid energy converters; Parts of machines, namely, Heat exchangers and conduits for fluid and heat transfer for integrated fuel cell power generation systems and subsystems in the nature of gas operated power generators; Integrated hydrogen-fuel systems comprised of heat exchangers being parts of aircraft engines, containers, valves as machine components, pumps for cooling engines and lines, namely, parts of machines, for propulsion systems for aircraft in the nature of aircraft engines; Hydrogen dispensing pumps for service filling stations; Parts for electrolysis machines for generating hydrogen, namely, separators and membranes for generators in the nature of electrolysis apparatus for generating hydrogen, circulation frames for generators, baffle plates and containers for generators, rectifier droplet separators for generators, and gas-liquid separators; Parts of machines, namely, Gas lines for discharging gas mixtures, hydrogen and water from drives for aircrafts in the nature of automated hydro-thrust cleaning units for pipelines; air filters for fuel cell systems Electronic transmission of data for use in regulating the fuel system and the fuel cell system and distributing the relevant data to the aircraft, a ground station or an internal memory Power generation; Power generation services; Custom manufacture, for others, of industrial and commercial hydrogen fuel and propulsion systems; Custom manufacture, for others, of fuel cell systems and hydrogen fuel and propulsion systems; Generation of hydrogen; Custom manufacture of fuel cell systems and hydrogen fuel and propulsion systems for others; providing information, advice and consultancy in relation to power generation services Microprocessor-based, control system comprised of microprocessors and downloadable computer software for controlling fuel cell operation; Hydrogen fuel cells; electronic Control system, for power generating fuel cell generator modules, comprised of computer hardware with an embedded operating system software, pressure relief valves for power generating, electric switches and electronic circuits; Test stations for fuel cells; Automatic test stations for fuel cells; downloadable computer software for use in operating test stations for fuel cells; downloadable computer software for use in operating automatic test stations for fuel cells; downloadable computer software for use in operating hydrogen test stations; Fuel cells; Fuel cell stacks; Integrated fuel cell systems comprised of fuel cells; Anodes and sensor devices, namely, temperature, humidity and pressure sensors in the nature of hygrometers; cathodes; Fuel cell stacks, heat sensors in the nature of hygrometers, pressure sensors and electronic controls, all for integrated fuel cell power generation systems and subsystems; pressure, heat and temperature sensors in the nature of heat detecting apparatus; computer hardware and downloadable software for controlling the integrated hydrogen fuel system in propulsion systems for aircraft Hydrogen cleaning devices, namely, gas scrubbers; Air filters for fuel cell systems Refueling aircraft with hydrogen; Construction of power generation plants; construction project management and construction supervision in the field of energy generation equipment Physical storage of hydrogen, for example with an integrated fuel system; Distribution of hydrogen and air as fuel for fuel cells; electricity supply through distribution of electricity; Distribution of energy; providing information, advice and consultancy in relation to the distribution and storage of energy Engineering services in the field of the refueling, storage and use of hydrogen as fuel, the conversion of hydrogen to electricity with fuel cells and the installation and integration of such systems, including their control by means of hardware and software; Consultancy in the field of design and development of test stations for fuel cells, fuel cells, integrated hydrogen fuel and propulsion systems, and ancillary equipment; Design of industrial and commercial hydrogen fuel and propulsion systems; Technical advice, research and development and testing services in the field of electricity, propulsion energy from hydrogen and hydrogen-fueled products; Testing services in the field of fuel cells, fuel cell systems, aerospace propulsion systems and hydrogen; Design and testing of hydrogen fuel and propulsion systems and fuel cells, fuel cell systems, aerospace propulsion systems based on fuel cell technologies; Design of alternative energy systems; Technical consultancy, engineering services and project development in the field of hydrogen fuel and drive systems and fuel cells, fuel cell systems, aviation drive systems based on fuel cell technologies; Information, advice and consultancy relating to all of the aforesaid; Technical project management in the field of energy generation engineering services and project development in the field of hydrogen fuel and propulsion systems and fuel cells, fuel cell systems, aviation propulsion systems based on fuel cell technologies; Information, advice and consultancy relating to all of the aforesaid; Technical project management in the field of energy generation engineering services and project development in the field of hydrogen fuel and propulsion systems and fuel cells, fuel cell systems, aviation propulsion systems based on fuel cell technologies; Providing information, advice and consultancy in relation to engineering design services; Technical project management in the field of energy generation
72.
METHOD FOR AVOIDING RESONANCE DAMAGE DURING CLEANING OF AN AT LEAST PARTLY ADDITIVELY MANUFACTURED COMPONENT, CLEANING DEVICE, MASS ELEMENT, AND SYSTEM
The invention is directed to a method for cleaning powder residues of an additive layer build-up method away from an at least partly additively manufactured component by a cleaning device, wherein a machine plate and the component arranged thereon are excited to mechanical oscillation during a cleaning process by a vibration actuator of the cleaning device with a set resonant frequency of the machine plate. According to the invention, before the cleaning process is carried out, a resonant frequency of the machine plate is set to the set resonant frequency by an arrangement of a mass element on a securing element of the machine plate.
The present invention relates to a method for inspecting a component, in particular a component of a turbomachine (1), including the steps of: capturing (S2) at least one X-ray or CT image of the component (10) using an image-capturing device (20); providing (S21) metadata about the component (10), the metadata including, in particular, a component type, a running time of the component (10), a number of remaining life cycles, and/or a repair history; classifying, by a machine learning system (30), the component (10) into a “serviceable” category or a “non-serviceable” category based on the image captured by the image-capturing device (20) and the provided metadata.
06 - Common metals and ores; objects made of metal
07 - Machines and machine tools
09 - Scientific and electric apparatus and instruments
11 - Environmental control apparatus
37 - Construction and mining; installation and repair services
38 - Telecommunications services
39 - Transport, packaging, storage and travel services
40 - Treatment of materials; recycling, air and water treatment,
42 - Scientific, technological and industrial services, research and design
Goods & Services
Storage systems for hydrogen consisting of metallic container for storing gases. Generators [power, emergency power], in particular for aircraft; Fuel cell energy converters [power generators]; Power generators based on integrated fuel cell hybrid energy converters; Heat exchangers and lines for liquid and heat transfer [parts of machines] for integrated fuel cell power generating systems and sub-systems [current generators]; Parts and fittings for all the aforesaid goods; Integrated hydrogen fuel systems consisting of containers, heat exchangers, valves, pumps, lines [parts of machines] for aircraft drives; Hydrogen dispensing pumps for service stations; Hydrogen generator parts, namely separators and membranes for generators, circulation frames for generators, end walls and boxes for generators, rectifying demisters for generators, gas liquid separators; Gas lines [parts of machines] for the drainage and discharge of gas mixtures, hydrogen and water from aircraft drives. Integrated fuel cell power generating systems and sub-systems, in particular for aircraft drives; hydrogen fuel cells; electricity-generating fuel cell power modules; Controllers, including the following products: Hardware and Software, Valves for the aforesaid goods, Switches and circuits for the aforesaid goods; fuel cell test stations; automated fuel cell test stations; computer software for use in fuel cell test stations; computer software for automated fuel cell test stations; computer software for hydrogen test stations; Fuel cells; fuel cell power systems; fuel cell stacks; integrated fuel cell systems; Anodes, Sensors, Cathodes, Waste traps; Membranes for hydrogen fuel cells; Hydrogen power storage systems; Parts fittings and accessories for all the aforesaid goods; Fuel cell stacks, sensors and electronic controllers for integrated fuel cell power generating systems and sub-systems; Sensor, hardware and software for regulating integrated hydrogen fuel systems in aircraft drives. hydrogen purifiers; rectifying demisters; Parts and fittings for all the aforesaid goods; Air fitters for fuel cell systems. Hydrogen fuelling services for aircraft; Construction of power generating plants; Construction project management services [building supervision] in the field of power generating installations. Electronic transmission of data for the purpose of fuel systems and fuel cell systems for regulation and distribution of the relevant data to aircraft, earth stations and internal storage. Filling containers for use in hydrogen fuel systems for aircraft; Hydrogen storage, for example with an integrated fuel system; Hydrogen and air distribution being fuel for fuel cells; Distribution of fluids for the distribution and draining of heat; Electricity supply and distribution; Distribution of energy; Information, advisory and consultancy services relating to all the foregoing. Electricity generating; Generation of power; Custom manufacture of industrial and commercial hydrogen fuel and drive systems; Custom manufacture of fuel cell systems and hydrogen fuel and drive systems; Hydrogen generation services; Custom manufacture of industrial and commercial hydrogen fuel and drive systems, for others; Information, consultancy and advisory services relating to the aforesaid. Engineering, in relation to the following services: Fuelling, storage and use of hydrogen being fuel, converting hydrogen to power with fuel cells and the installation and integration of the aforesaid systems, including regulation through hardware and software; Consultancy in the field of design and development of fuel cell test stations, fuel cells, integrated hydrogen fuel and drive systems and ancillary equipment; Design of industrial and commercial hydrogen fuel and drive systems; Technical consultancy, research and development and the provision of examinations, in relation to the following goods: Electric/drive power of hydrogen and with hydrogen powered goods; Provision of examinations relating to fuel cells, fuel cell systems, [aviation] drive systems and hydrogen; Design, examination of hydrogen fuel and drive systems and fuel cells, fuel cell systems, [aviation] drive systems based on fuel cell technologies; designing alternate energy systems; Technical consultancy, Engineering and Project development, in the following fields: Hydrogen fuel and propulsion systems and Fuel batteries, Fuel cell systems, [aviation] propulsion systems based on fuel cell technologies; Information, consultancy and advisory services relating to the aforesaid; Engineering project management services, in the following fields: Production of energy.
06 - Common metals and ores; objects made of metal
07 - Machines and machine tools
09 - Scientific and electric apparatus and instruments
11 - Environmental control apparatus
37 - Construction and mining; installation and repair services
38 - Telecommunications services
39 - Transport, packaging, storage and travel services
40 - Treatment of materials; recycling, air and water treatment,
42 - Scientific, technological and industrial services, research and design
Goods & Services
Storage systems for hydrogen consisting of metallic container for storing gases. Generators [power, emergency power], in particular for aircraft; Fuel cell energy converters [power generators]; Power generators based on integrated fuel cell hybrid energy converters; Heat exchangers and lines for liquid and heat transfer [parts of machines] for integrated fuel cell power generating systems and sub-systems [current generators]; Parts and fittings for all the aforesaid goods; Integrated hydrogen fuel systems consisting of containers, heat exchangers, valves, pumps, lines [parts of machines] for aircraft drives; Hydrogen dispensing pumps for service stations; Hydrogen generator parts, namely separators and membranes for generators, circulation frames for generators, end walls and boxes for generators, rectifying demisters for generators, gas liquid separators; Gas lines [parts of machines] for the drainage and discharge of gas mixtures, hydrogen and water from aircraft drives. Integrated fuel cell power generating systems and sub-systems, in particular for aircraft drives; hydrogen fuel cells; electricity-generating fuel cell power modules; Controllers, including the following products: Hardware and Software, Valves for the aforesaid goods, Switches and circuits for the aforesaid goods; fuel cell test stations; automated fuel cell test stations; computer software for use in fuel cell test stations; computer software for automated fuel cell test stations; computer software for hydrogen test stations; Fuel cells; fuel cell power systems; fuel cell stacks; integrated fuel cell systems; Anodes, Sensors, Cathodes, Waste traps; Membranes for hydrogen fuel cells; Hydrogen power storage systems; Parts fittings and accessories for all the aforesaid goods; Fuel cell stacks, sensors and electronic controllers for integrated fuel cell power generating systems and sub-systems; Sensor, hardware and software for regulating integrated hydrogen fuel systems in aircraft drives. hydrogen purifiers; rectifying demisters; Parts and fittings for all the aforesaid goods; Air fitters for fuel cell systems. Hydrogen fuelling services for aircraft; Construction of power generating plants; Construction project management services [building supervision] in the field of power generating installations. Electronic transmission of data for the purpose of fuel systems and fuel cell systems for regulation and distribution of the relevant data to aircraft, earth stations and internal storage. Filling containers for use in hydrogen fuel systems for aircraft; Hydrogen storage, for example with an integrated fuel system; Hydrogen and air distribution being fuel for fuel cells; Distribution of fluids for the distribution and draining of heat; Electricity supply and distribution; Distribution of energy; Information, advisory and consultancy services relating to all the foregoing. Electricity generating; Generation of power; Custom manufacture of industrial and commercial hydrogen fuel and drive systems; Custom manufacture of fuel cell systems and hydrogen fuel and drive systems; Hydrogen generation services; Custom manufacture of industrial and commercial hydrogen fuel and drive systems, for others; Information, consultancy and advisory services relating to the aforesaid. Engineering, in relation to the following services: Fuelling, storage and use of hydrogen being fuel, converting hydrogen to power with fuel cells and the installation and integration of the aforesaid systems, including regulation through hardware and software; Consultancy in the field of design and development of fuel cell test stations, fuel cells, integrated hydrogen fuel and drive systems and ancillary equipment; Design of industrial and commercial hydrogen fuel and drive systems; Technical consultancy, research and development and the provision of examinations, in relation to the following goods: Electric/drive power of hydrogen and with hydrogen powered goods; Provision of examinations relating to fuel cells, fuel cell systems, [aviation] drive systems and hydrogen; Design, examination of hydrogen fuel and drive systems and fuel cells, fuel cell systems, [aviation] drive systems based on fuel cell technologies; designing alternate energy systems; Technical consultancy, Engineering and Project development, in the following fields: Hydrogen fuel and propulsion systems and Fuel batteries, Fuel cell systems, [aviation] propulsion systems based on fuel cell technologies; Information, consultancy and advisory services relating to the aforesaid; Engineering project management services, in the following fields: Production of energy.
76.
GEARED TURBOFAN LOW-PRESSURE TURBINE WITH FLAT HUB
A geared turbofan engine includes a plurality of turbine stages, wherein for each stage (i) of the turbine, an inner radius Ri has a maximum deviation between +1.5% and −3% as compared to the average inner radius of the inner blade platforms of the plurality of stages. The engine further includes a fan, the fan coupled to the turbine stages via a gear.
F02K 3/06 - 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 the plant including ducted fans, i.e. fans with high volume, low-pressure outputs, for augmenting jet thrust, e.g. of double-flow type with front fan
09 - Scientific and electric apparatus and instruments
35 - Advertising and business services
37 - Construction and mining; installation and repair services
42 - Scientific, technological and industrial services, research and design
Goods & Services
Generators for aircraft, Compressors; Transmission and propulsion couplings and components (except for land vehicles); Propulsive and non-propulsive power systems machines, For use with the following goods: Aircraft and components thereof included in this class, including turbines, motors and engines, propellers, engine cars, thrust reversers; Auxiliary power units for air vehicles (machines); Lubrication systems for engines and turbines of air vehicles (machines); Test benches for engines, turbines and other propellers (machines) for aircraft. Electric and electronic apparatus and instruments, namely generators and/or starters for static or mobile installations for aircraft; Electric, electronic and magnetic pressure, speed, motion, temperature, position and vibration sensors; Electronic systems, apparatus and equipment, whether on-board or not, for the acquisition and processing of parameters and data; Electric and electronic hardware and equipment for maintaining and controlling generators, starters and integrated assemblies for the generation of propulsive and non-propulsive power. Services in connection with the sale of the following goods: Propulsive and non-propulsive power systems (machines) for aircraft; Administrative and commercial management of parts and spare parts for users of engines, systems, equipment and parts for aircraft; Business organisation consultancy, in relation to the following fields: Aircraft propulsion systems, turbines. Repair, overhaul, Maintenance and Maintenance, In connection with the following goods: Propulsive and non-propulsive power systems (machines) for aircraft and components therefor, including turbines, motors and engines, propellers, engine cars, thrust inverters; Consultancy relating to the identification and selection of tools for the repair, servicing, upkeep, standardisation and maintenance of systems, equipment and parts for aeronautical vehicles. Technical, scientific and industrial research; Engineering services; Research and development (engineering) in the field of aeronautics; Analysis of technical data; Engineering in relation to evaluation, assessment and research in connection with technologies used in aeronautical vehicle systems, equipment and parts; Testing of machines and materials; Computer software design and computer programming; Analysis and surveying of equipment and parts for aircraft; Analysis, surveying and processing of the acquisition of data recorded during the operation of engines, systems, equipment and parts for aircraft; Conducting technical project studies, In connection with the following goods: Air vehicles and components therefor, including motors and engines, engine cars, reactors, propellers or reverse thrusters, air vehicles.
The invention relates to an aircraft fuel cell propulsion unit (10) comprising a fuel cell system (12) that includes at least one anode (14), at least one cathode (15) and a process gas device (17) for supplying fuel and ambient air to the anode (14) and the cathode (15) and evacuating spent process gases, further comprising a ram air duct (21) through which compressed ram air (22) flows, and a heat exchanger (20) which is located in the ram air duct (21) and is designed to give off heat generated by the fuel cell system (12) to the environment.
H01M 8/04119 - Arrangements for control of reactant parameters, e.g. pressure or concentration of gaseous reactants with simultaneous supply or evacuation of electrolyteHumidifying or dehumidifying
79.
Braze alloy mix for application in a method for brazing a component, additive alloy, brazing method, and component
The invention relates to a braze alloy mix for application in a method for brazing a component that has a nickel-based superalloy as base material, wherein the braze alloy mix comprises the following powders in a predetermined mixing ratio: a powder of a first braze alloy, a powder of a second braze alloy, a powder of a third braze alloy, and a powder of an additive alloy.
A cooling system (10) for an aircraft is provided, in particular for cooling at least one element of an electric propulsion system (24) of the aircraft, the cooling system (10) being at least partially disposed within a wing (12) of the aircraft and including at least two heat exchangers (16, 42) interconnected via at least one cooling circuit (11), the first heat exchanger (16) being operatively connected to the at least one element to be cooled of the electric propulsion system (24), and the second heat exchanger (42) being disposed within at least one wing (12) and being operatively connected to an upper and/or lower wing shell (46, 48) of the wing (12). A method for cooling at least one element of an electric propulsion system (24) of an aircraft is also provided.
B64D 33/08 - Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of power plant cooling systems
B60L 58/33 - Methods or circuit arrangements for monitoring or controlling batteries or fuel cells, specially adapted for electric vehicles for monitoring or controlling fuel cells for controlling the temperature of fuel cells, e.g. by controlling the electric load by cooling
The present invention relates to a propulsion system (1) for an aircraft (50), having a first propulsion unit (11) which has a first power generator (21) for outputting a first electric power (P1) and a first thrust unit (31) connected to the first power generator (21) to generate thrust from the first electric power (P1), and a second propulsion unit (12) which has a second power generator (22) for outputting a second electric power (P2) and a second thrust unit (32) connected to the second power generator (22) to generate thrust from the second electric power (P2), and a connecting device (40), which, in the event of a fault of the first propulsion unit (11), is designed to connect the first thrust unit (31) or the first power generator (21) to the second propulsion unit (12) for supply.
B64D 27/24 - Aircraft characterised by the type or position of power plants using steam or spring force
B64D 27/02 - Aircraft characterised by the type or position of power plants
82.
HOUSING FLANGE FOR AN ELECTRIC MOTOR HOUSING OF AN ELECTRIC MOTOR, ASSEMBLY COMPRISING A HOUSING FLANGE AND STATOR TEETH, AND METHOD FOR MANUFACTURING A HOUSING FLANGE
The invention relates to a housing flange (1) for an electric motor housing (2) of an electric motor (3), in particular for an aircraft engine, the housing flange (1) comprising a forged and/or cast round base plate (4), the base plate (4) comprising a through-opening (5) in its centre for the passage of a shaft (6) of a rotor (8) of the electric motor (3). According to the invention, a housing coolant distribution body (10), which is additively manufactured at least in some regions, is located on a first base plate main surface (9) of the base plate (4), the housing coolant distribution body (10) being in the form of a hollow cylinder, the cylinder axis (11) of which is oriented so as to be centred with respect to the through-opening (5), and the housing coolant distribution body (10) comprising one or more coolant channels (16) for the passage of a coolant.
A method for automatically generating an optimized maintenance plan for a fleet of aircraft engines, includes the steps of: acquiring input data on a plurality of engines and providing an existing initial maintenance plan or creating an initial maintenance plan based on the acquired input data. A total maintenance effort for the fleet resulting in an application of the initial maintenance plan is then determined. Next, the engines are sorted into a defined order according to at least one criterion and at least one optimization strategy or heuristic stored as an algorithm in a computer program is applied to each of the engines in the defined order. Next, an optimized maintenance plan for the engines or output data comprising an estimated total maintenance effort of the optimized maintenance plan is output.
A rotor blade (20) for a rotor blade assembly (10) of a turbomachine (1) is provided, having an inner rotor blade platform (40) which extends axially from the rotor blade (20) with respect to a longitudinal turbomachine axis (2) and has two opposite circumferential end faces (41) and a free axial end (42) whose cross section is radially inwardly and radially outwardly bounded by circular arcs of two concentric circles. The inner rotor blade platform (40) has a cross section of connection (45) with the rotor blade (20) which is bounded radially inwardly by an inner connecting line (46) and radially outwardly by an outer connecting line (47). Each of the connecting lines (46, 47) has a central portion (61) having a convex curvature.
The present invention relates to a fuel cell stack (1), having fuel cells (2) arranged successively in a stacking direction (3), an inner covering element (11) which follows the fuel cells (2) in the stacking direction (3), and an outer covering element (12) which follows the inner covering element (11) in the stacking direction (3) and holds the inner covering element and the fuel cells (2) together in a braced state, wherein the outer covering element (12) forms at least a first and a second spring element (15.1, 15.2) perpendicularly to the stacking direction (3), wherein each of the spring elements (15.1, 15.2) forms an arc profile (16.1, 16.2) which is convexly curved in the direction of the inner covering element (11), and the respective arc profile (16.1, 16.2) is separately suspended, and wherein the inner covering element (11) forms a respective receptacle (40.1, 40.2) for the spring elements (15.1, 15.2), each receptacle being concavely curved in the direction of the outer covering element (12) and accommodating the respective convexly curved arc profile (16.1, 16.2).
The invention relates to a fuel cell stack (1) with fuel cells (2) arranged one after another in a stacking direction (3), a cover element (5) and a hydraulic compensation element (6), wherein the hydraulic compensation element (6) and the cover element (5) are arranged following the fuel cells (2) in the stacking direction (3), wherein the cover element (5) holds the fuel cells (2) together in a state (21) in which it compresses the fuel cells (2), and is curved towards the fuel cells (2) in an uncompressed state (20), and wherein the hydraulic compensation element (6) is/can be applied with a fluid (11) in order to adjust a pressing force (8) transferred to the fuel cells (2) in the compressed state (21).
The invention relates to a compressor for an engine, wherein the compressor has compressor stages arranged in succession in a flow direction of the compressor and each compressor stage has a rotating blade cascade and a guide vane cascade arranged downstream of the rotating blade cascade and the rotating blade cascade and the guide vane cascade each have an aspect ratio.
F02C 3/06 - Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising only axial stages
A method (100) for operating an aircraft-engine turbomachine (1) having a compressor (3), through which a gas flow (6) passes in a flow direction, a combustion chamber (4), a turbine (5) and a heat exchanger (8) downstream of the turbine (5), wherein the heat exchanger (8) generates steam from water by means of energy from the gas flow (6) and the steam is fed, in particular together with fuel, into the gas flow (6) for burning in the combustion chamber (4).
The invention relates to a propulsion system (1) for an aircraft, comprising a gas turbine (2) having a core flow channel (10), wherein a compressor (12), a combustion chamber (13), a first turbine, in particular a high-pressure turbine (14), for driving the compressor (12), and a second turbine, in particular a low-pressure turbine (15) are arranged in the core flow channel (10) in the flow direction, and comprising a water system (30) for providing water via recovery from an exhaust gas from the core flow channel (10).
F02C 3/30 - Adding water, steam or other fluids to the combustible ingredients or to the working fluid before discharge from the turbine
F02C 7/141 - Cooling of plants of fluids in the plant of working fluid
F02K 3/06 - 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 the plant including ducted fans, i.e. fans with high volume, low-pressure outputs, for augmenting jet thrust, e.g. of double-flow type with front fan
F02K 3/115 - Heating the by-pass flow by means of indirect heat exchange
The invention relates to a heat exchanger (10) for cooling a hot fluid, in particular an exhaust gas or a fuel-cell cooling fluid, by means of a cooling fluid which is at a lower temperature than the hot fluid and which has a high flow velocity, comprising a high-temperature grille (30) for guiding the hot fluid and a low-temperature grille (20) for guiding the cooling fluid. According to the invention, a heat exchanger which can improve a transfer of heat despite a high-velocity inflowing fluid and/or which can reduce the required installation space is created in that a diffuser region (24) for decelerating the cooling fluid is arranged in at least one first low-temperature channel (21), through which the cooling fluid flows, of the low-temperature grille (20), and in that the diffuser region (24) and a first high-temperature channel (31), through which the hot fluid flows, of the high-temperature grille (30) have at least one shared wall (40) for heat transfer.
F28F 1/02 - Tubular elements of cross-section which is non-circular
F28F 13/08 - Arrangements for modifying heat transfer, e.g. increasing, decreasing by affecting the pattern of flow of the heat-exchange media by varying the cross-section of the flow channels
F28D 21/00 - Heat-exchange apparatus not covered by any of the groups
A propulsion system (1) for an aircraft, comprising a gas turbine (2), with a main flow duct (10) and a bypass flow duct (20), wherein the gas turbine (2) has an outer housing (5) which surrounds the bypass flow duct (20) on the outside. The core flow of the gas turbine (2) is routed radially to the outside and at least in portions through the outer housing (5) or along the outer housing (5).
The invention relates to a propulsion system (1) for an aircraft, comprising a gas turbine (2) with a main flow channel (10) and a bypass flow channel (20), a water system (30) and a steam system (40), wherein the water system (30) comprises at least one water separation unit (31) and a condenser (21) with at least one condenser module (23), wherein the gas turbine (2) has a housing (5, 6), in particular an outer housing (5) bordering the bypass flow channel (20) on the outside, and/or an inner housing (6) comprising the main flow channel (10). A propulsion system, with a water and steam system that is better integrated into the gas turbine, is achieved in that the water separation unit (13) is arranged in and/or on the outer housing (5), in particular in the cowling, and/or the at least one condenser module (23) is arranged in the bypass flow channel (20) and has exhaust gas channels (26) which direct an exhaust gas from the main flow channel (10), via the the bypass flow channel (20) and in and/or through the outer housing (5).
F02C 3/30 - Adding water, steam or other fluids to the combustible ingredients or to the working fluid before discharge from the turbine
F02K 3/115 - Heating the by-pass flow by means of indirect heat exchange
F02C 7/141 - Cooling of plants of fluids in the plant of working fluid
F02K 3/06 - 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 the plant including ducted fans, i.e. fans with high volume, low-pressure outputs, for augmenting jet thrust, e.g. of double-flow type with front fan
93.
EXHAUST GAS TREATMENT APPARATUS FOR AN AIRCRAFT ENGINE
The invention relates to an exhaust gas treatment apparatus (1) for an aircraft engine (2), the exhaust gas treatment apparatus comprising an exhaust gas channel (7), through which an exhaust gas of the aircraft engine (2) can flow, a first cooling device (8) and a second cooling device (13) for cooling an exhaust gas flow (6) flowing through the exhaust gas channel (7), the second cooling device (13) being located downstream of the first cooling device (8) with respect to the exhaust gas flow (6). The invention also relates to a method for operating such a cooling device.
F01N 3/04 - Exhaust or silencing apparatus having means for purifying, rendering innocuous, or otherwise treating exhaust for cooling, or for removing solid constituents of, exhaust by means of liquids
94.
Guide vane device, mounting tool, as well as turbomachine and method for mounting and dismantling the guide vane device
The invention is directed to a guide vane device for a guide vane adjustment of a turbomachine, comprising a guide vane, which has a shaft extending along an adjustment axis of the guide vane, as well as an adjusting lever, which forms a connecting element for connection to an outer end of the shaft, wherein, at its outer end, the shaft has a three-dimensional front surface with at least one beveled region, the connecting element surrounds, at least in sections, the outer end of the shaft in a sleeve-like manner and is joined to the outer end in a form-fitting manner, and the guide vane device forms an interference fit between the connecting element and the outer end of the shaft.
An airfoil array segment for an airfoil array of a turbomachine including a platform having a platform surface and an upstream-side platform edge, as well as at least two airfoils, whose leading and trailing edges define an inter-airfoil strip, the platform surface having a trough with a bottom configured such that the bottom is a global minimum and a radial position of the trough decreases relative to a reference surface in the circumferential direction from a suction side of one of the airfoils toward the pressure side of the adjacent other airfoil toward the bottom and from there increases in the circumferential direction, at most up to the radial position of the reference surface, and a radial position of the trough decreasing relative to a reference surface axially in the downstream direction toward the bottom and from there increasing axially in the downstream direction, at most up to the radial position of the reference surface, and the platform surface reaching at most a radial position of the reference surface, the reference surface corresponding to an uncontoured platform surface.
A heat engine, in particular an aircraft engine, having a first compressor for supplying a combustion chamber of the heat engine with air and a first turbine arranged downstream of the combustion chamber for driving the first compressor, wherein the heat engine also has at least one steam supply line for supplying steam from a steam source into the combustion chamber. The heat engine also has a steam supply device, which has a second compressor and is designed to compress the working gas further by the second compressor as a function of a mass flow conducted through the steam supply line, before the working gas flows into the combustion chamber.
The invention relates to a device and a method for cooling a heat exchanger of a fuel cell of a flight propulsion drive outside of a flight phase of an aircraft. The flight propulsion drive has an air line with at least one compressor for feeding compressed air for the operation of the fuel cell. A flow amplifier is arranged in the region of the heat exchanger, and is configured to guide air onto a cooling surface of the heat exchanger, whereby thermal energy is diverted from the cooling surface of the heat exchanger.
B64D 33/08 - Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of power plant cooling systems
H01M 8/04007 - Auxiliary arrangements, e.g. for control of pressure or for circulation of fluids related to heat exchange
H01M 8/04111 - Arrangements for control of reactant parameters, e.g. pressure or concentration of gaseous reactants using a compressor turbine assembly
98.
BLADE FOR A TURBOMACHINE INCLUDING BLADE TIP ARMOR AND AN EROSION PROTECTION LAYER, AND METHOD FOR MANUFACTURING SAME
blade for a turbomachine is provided. The blade at its blade tip (4) includes blade tip armor (5), and an erosion protection layer (11) above the blade tip armor. For the blade, the erosion protection layer in the area of the blade tip has a layer thickness in the range of 5 µm to 100 µm, in particular 10 µm to 50 µm.
The invention relates to a masking device (1) for producing a masking structure (2) on a turbomachine component (3) to be machined by means of a surface finishing method. The masking device (1) operates in an automated and adaptive manner and is configured to move at least one metering unit (8) of the masking device (1) along a predetermined masking zone of the component (3) by an application robot arm (14) of the masking device (1) in an application method step (S3), and thereby apply a first masking layer (37) of a masking agent (11) in the masking zone by means of the metering unit (8), and in a curing method step (S4) after completion of the application method step (S3), to irradiate the applied first masking layer at least in areas by an irradiation means of the masking device (1) in order to cure the masking agent (11) of the masking layer, and to repeat the application method step (S3) and the curing method step (S4) in order to produce further masking layers of the masking structure (2) until the masking structure (2) is completed.
B05C 5/02 - Apparatus in which liquid or other fluent material is projected, poured or allowed to flow on to the surface of the work from an outlet device in contact, or almost in contact, with the work
B05C 9/12 - Apparatus or plant for applying liquid or other fluent material to surfaces by means not covered by groups , or in which the means of applying the liquid or other fluent material is not important for applying liquid or other fluent material and performing an auxiliary operation the auxiliary operation being performed after the application
B05B 12/20 - Masking elements, i.e. elements defining uncoated areas on an object to be coated
B05B 13/04 - Means for supporting workArrangement or mounting of spray headsAdaptation or arrangement of means for feeding work the spray heads being moved during operation
B05D 1/32 - Processes for applying liquids or other fluent materials using means for protecting parts of a surface not to be coated, e.g. using stencils, resists
100.
Exhaust-gas treatment device for an aircraft engine
The present invention relates to an exhaust-gas treatment device for an aircraft engine, comprising an exhaust-gas channel, through which an exhaust gas of the aircraft engine flows, and a first cooling unit for cooling with ambient air, characterized by a second cooling unit, which is downstream of the first cooling unit with respect to an exhaust-gas flow in the exhaust-gas channel.
F01N 3/02 - Exhaust or silencing apparatus having means for purifying, rendering innocuous, or otherwise treating exhaust for cooling, or for removing solid constituents of, exhaust
F01N 13/08 - Other arrangements or adaptations of exhaust conduits
F02C 3/30 - Adding water, steam or other fluids to the combustible ingredients or to the working fluid before discharge from the turbine
