An electric drive system (1A-1D) comprises an electric motor (10; 10A, 10B) having a rotor (100) and a plurality of lanes (101A-101D) which are electrically isolated from one another and to which electric current can be applied independently of one another in order to drive the rotor (100); a respective supply unit (11) for each of the lanes (101A-101D); and a control system (12) which is designed to simultaneously operate at least one of the lanes (101A-101D) in a motor mode in which electric current is applied to the lane (101A-101D) via the corresponding supply unit (11) in order to convert electrical energy into kinetic energy of the rotor (100) and operate at least one of the lanes (101A-101D) in a generator mode in which electric current is provided by means of the lane (101A-101D) via the corresponding supply unit (11).
H02P 5/74 - Arrangements specially adapted for regulating or controlling the speed or torque of two or more electric motors controlling two or more AC dynamo-electric motors
B60L 3/00 - Electric devices on electrically-propelled vehicles for safety purposesMonitoring operating variables, e.g. speed, deceleration or energy consumption
B60L 58/21 - Methods or circuit arrangements for monitoring or controlling batteries or fuel cells, specially adapted for electric vehicles for monitoring or controlling batteries of two or more battery modules having the same nominal voltage
A computer-implemented method for determining one or more properties associated with a shroud gap of a turbine includes obtaining a plurality of image frames of shroud gaps, wherein the turbine is in a different orientation in each frame, and a first reference image of a first shroud gap in a first orientation. For each shroud gap may be identified based on the first reference image, an image frame in which an orientation of the shroud gap matches the first orientation. Image processing may be performed on the identified frames to identify a first region of that frame associated with a shroud gap. The identified regions of the frames may be combined to obtain a gap mask. The gap mask may be applied on each identified frame to identify a second region and image processing may be performed on the second region to determine the properties associated with the shroud gap.
G06T 5/50 - Image enhancement or restoration using two or more images, e.g. averaging or subtraction
G06T 5/20 - Image enhancement or restoration using local operators
G06T 7/70 - Determining position or orientation of objects or cameras
G06V 10/25 - Determination of region of interest [ROI] or a volume of interest [VOI]
G06V 10/764 - Arrangements for image or video recognition or understanding using pattern recognition or machine learning using classification, e.g. of video objects
A fuel system (300) for a gas turbine engine (203). The fuel system comprises a fuel offtake (302) configured to divert a portion of hydrogen fuel from a main fuel conduit (217), a burner (218) configured to burn the portion of hydrogen fuel diverted from the main fuel conduit (217) and at least first and second heat exchangers (306, 310). The first heat exchanger (306) is configured to transfer heat from exhaust gasses produced by the burner (218) to hydrogen fuel in the main fuel conduit (217) and the second heat exchanger (310) is provided upstream in hydrogen flow of the first heat exchanger (306) and is configured to transfer heat from a further heat exchange fluid to hydrogen fuel in the main fuel conduit (217). In an embodiment, the further heat exchange fluid is compressor bleed air bled from a core compressor of the gas turbine engine.
A fuel spray nozzle for a gas turbine engine includes a feed arm, a fuel tube, a sleeve, and a nozzle head. The feed arm includes a housing. The fuel tube is disposed within the housing and spaced apart from the housing, such that the housing and the fuel tube define an air gap therebetween. The sleeve is disposed within the air gap and spaced apart from the housing. The sleeve at least partially engages with the fuel tube and surrounds at least a portion of the fuel tube along a tube axis. The sleeve is movably disposed around the fuel tube, such that the sleeve and the fuel tube are movable relative to each other along the tube axis. The nozzle head is fluidly connected to the fuel tube and configured to receive the fuel from the fuel tube.
F23R 3/28 - Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
F23D 11/12 - Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space the spraying being induced by a gaseous medium, e.g. water vapour characterised by the shape or arrangement of the outlets from the nozzle
Computer-implemented methods and apparatuses for blade monitoring are described. An example method comprises obtaining an image of at least a part of a blade and analysing the obtained image to detect portions of the image showing a part of a blade. The example method further comprises determining, using information on the detected portions of the image, the position of the blade relative to a imaging device used to obtain the image of at least a part of the blade, and comparing the determined position with a reference position. The example method also comprises determining a positional suitability of the imaging device position, based on the comparison, and outputting positional suitability information.
A gear pump assembly includes an inlet configured to receive a fluid, an outlet, a main drive shaft, a secondary gear stage, and a primary gear stage configured to pump the fluid from the inlet to the outlet. The secondary gear stage includes a secondary driver gear driven by the main drive shaft, a secondary driver bearing block disposed adjacent to and supporting the secondary driver gear, a secondary driven gear meshed with and driven by the secondary driver gear, a secondary driven bearing block disposed adjacent to and supporting the secondary driven gear, and a driver bore portion receiving the secondary driver bearing block therein. A fluid passage fluidly communicates the primary gear stage with the driver bore portion.
F04C 2/08 - Rotary-piston machines or pumps of intermeshing-engagement type, i.e. with engagement of co-operating members similar to that of toothed gearing
Aircraft power and propulsion systems and methods thereof; an aircraft power and propulsion system includes: a gas turbine engine having first and second spools; one or more electrical networks; a first electrical machine joined with the first spool; a second electrical machine joined with the second spool; a first power converter having first and second sides; a second power converter having first and second sides; and a controllable switching arrangement in which a connection to the first side of the second power converter is switchable between: a winding of the second electrical machine, or the winding of the first electrical machine.
A method for scanning a component includes applying a contrast agent to one or more regions of interest of the component. The method further includes providing a computed tomography scanner including an x-ray source and a detector. The method further includes placing the component between the x-ray source and the detector. The method further includes generating, via the x-ray source, an x-ray cone beam or fan beam that passes through the component. The method further includes receiving the x-ray cone beam or fan beam at the detector and generating an x-ray image of the component.
G01N 23/046 - Investigating or analysing materials by the use of wave or particle radiation, e.g. X-rays or neutrons, not covered by groups , or by transmitting the radiation through the material and forming images of the material using tomography, e.g. computed tomography [CT]
A fuel system for a gas turbine engine includes a fuel offtake configured to divert a portion of hydrogen fuel from a main fuel conduit, a burner configured to burn the portion of hydrogen fuel diverted from the main fuel conduit and at least first and second heat exchangers. The first heat exchanger is configured to transfer heat from exhaust gasses produced by the burner to hydrogen fuel in the main fuel conduit and the second heat exchanger is provided upstream in hydrogen flow of the first heat exchanger and is configured to transfer heat from a further heat exchange fluid to hydrogen fuel in the main fuel conduit. In an embodiment, the further heat exchange fluid is compressor bleed air bled from a core compressor of the gas turbine engine.
F02C 7/224 - Heating fuel before feeding to the burner
F02C 3/22 - Gas-turbine plants characterised by the use of combustion products as the working fluid using a special fuel, oxidant, or dilution fluid to generate the combustion products the fuel or oxidant being gaseous at standard temperature and pressure
An aircraft power and propulsion system includes a gas turbine engine having first and second spools, the first spool being a starting spool; first and second DC electrical networks having first and second operating voltages; a first electrical machine joined with the first spool, the first electrical machine having first and a second winding sets; a second electrical machine joined with the second spool; a first, second and third AC:DC converter; and a controllable switching arrangement configured so that a connection to an AC-side of the third AC:DC converter is switchable between a winding of the second electrical machine or the second DC electrical network via an inductor.
Methods and apparatus for analysing images are described. In an example, processor circuitry receives data comprising three-dimensional (3D) data and two-dimensional (2D) data. The 2D data comprises a subject image of a subject element of a component, and the 3D data comprises data representing a geometry of a reference element of the component. The method further comprises determining a mapping between the subject image and the 3D data, wherein locations in the subject image are mapped to locations in 3D space and determining a measurement of a property of the subject element using the mapping.
A bearing block adapted for use in a gear pump assembly. The bearing block includes a bearing surface configured to face one or more gears. The bearing block further includes a bearing block body formed with a recess. The bearing block further includes an insert located within the recess. The insert includes an insert body including an outer surface. The insert body has a tapered shape that tapers outwardly from the bearing surface. The insert further includes a plurality of ridges disposed on the outer surface. The plurality of ridges defines one or more grooves therebetween. The recess includes a tapered shape complementary to the tapered shape of the insert body, such that the insert body engages with the bearing block body.
F04C 2/08 - Rotary-piston machines or pumps of intermeshing-engagement type, i.e. with engagement of co-operating members similar to that of toothed gearing
F04C 2/18 - Rotary-piston machines or pumps of intermeshing-engagement type, i.e. with engagement of co-operating members similar to that of toothed gearing of other than internal-axis type with toothed rotary pistons with similar tooth forms
13.
METHOD AND CONTROLLER FOR CONTROLLING A VAPOUR-COMPRESSION SYSTEM WITH THERMODYNAMIC CONSTRAINTS SATISFACTION
A method of controlling a vapour-compression system for circulating a working fluid. The vapour-compression system comprises a compressor, an expansion device and an evaporator configured to facilitate heat transfer from a thermal source into the working fluid. The method comprises: determining or receiving a cooling demand, the cooling demand being associated with a demand to cool the thermal source; determining a preliminary thermofluidic property objective value based on the cooling demand; determining a final thermofluidic property objective value based on the preliminary thermofluidic property objective value and one or more thermofluidic property objective value thresholds, wherein the final thermofluidic property objective value relates to a target thermofluidic property of the working fluid at a control location within the vapour-compression system; and controlling at least one of the compressor and the expansion device based on the final thermofluidic property objective value.
An imaging system for a component to be imaged, the imaging system comprising a frame having an upper and lower section, at least one section comprising a clamp for holding the component, the frame supporting an camera container, wherein the camera container comprises a box having at least one white light source and a diffuser and at least one camera, and wherein the camera is connected to a computer.
An assembly adapted for use in a gas turbine engine includes a blade track segment, a carrier segment, and a retainer. The blade track segment defines a portion of a gas path of the gas turbine engine. The carrier segment supports the blade track segment to locate the blade track segment radially outward of the axis. The retainer couples the blade track segment to the carrier segment. The carrier segment may include a plurality of impingement passageways to conduct cooling air to the blade track segment.
A turbine assembly adapted for use with a gas turbine engine includes a turbine shroud assembly and a turbine vane. The turbine shroud assembly includes a blade track segment arranged circumferentially at least partway around an axis of the gas turbine engine, a carrier segment arranged circumferentially at least partway around the axis, and a mount assembly configured to couple the blade track segment to the carrier segment. The turbine vane is located axially aft of the turbine shroud assembly and helps retain the mount assembly in place.
Rolls-Royce High Temperature Composites Inc. (USA)
Inventor
Thomas, David J.
Downie, Christopher
Sippel, Aaron D.
Freeman, Ted J.
Snyder, Clark
Abstract
A turbine shroud assembly adapted for use with a gas turbine engine includes a shroud segment. The shroud segment includes a heat shield, an attachment flange, and a multi-layer coating. The heat shield extends circumferentially partway around the axis to define a portion of gas path for the gas turbine engine. The attachment feature extends radially outward from the heat shield. The multi-layer coating is applied to different surfaces of the heat shield and the attachment feature of the shroud segment.
F01D 25/24 - CasingsCasing parts, e.g. diaphragms, casing fastenings
F01D 5/28 - Selecting particular materialsMeasures against erosion or corrosion
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
F01D 25/00 - Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
A hydrogen fueled aircraft including a fuselage and a wing, and at least one fuel tank. The hydrogen fuel tank is mounted to the wing, wherein the fuel tank is mounted above the wing and spaced from an upper surface of the wing by a tank mounting arrangement which does not interfere with the wing upper surface.
A particulate sample collector for collecting a particulate sample deposited on a surface of a gas turbine engine component. The particulate sample collector comprises a collection media support, itself comprising a support surface that supports a collection media between an inlet of the particulate sample collector and an exit of the particulate sample collector. The inlet is comprised within the hollow body. The inlet and exit are fluidically coupled. The exit is comprised within either the hollow body or the collection media support. An airflow carrying the particulate sample enters the particulate sample collector at the inlet, so that the collection media collects the particulate sample. The airflow then exits the particulate sample collector at the exit.
A method includes: determining first atmospheric agents that are predicted to be ingested by a gas turbine engine during operation in a predefined route of an aircraft and their composition, particle size, and concentration; determining a composition and an amount of a predicted deposit that is predicted to form on the component based on the composition, the particle size, and the concentration of the first atmospheric agents; determining a predicted damage to the component based at least on the composition and the amount of the predicted deposit and a composition of a coating of the component; determining locations at which second atmospheric agents are present in air that reduce the predicted damage to the component and their composition, particle size, and concentration; determining an alternative route including the locations; and operating the gas turbine engine at the locations in the alternative route.
A method for detecting a burner failure in a gas turbine engine that has a combustor and a turbine disposed downstream of the combustor. The combustor has a plurality of burners arranged annularly. The method includes providing a plurality of temperature sensors arranged annularly at an outlet of the turbine; obtaining a plurality of temperature signals from the plurality of temperature sensors; determining a plurality of validated temperature signals from the plurality of temperature signals; determining a temperature focus at least based on the plurality of validated temperature signals; improving the temperature focus such that the temperature focus is within a tolerance range; and performing at least one hazard protection action at least when the temperature focus crosses a predetermined threshold.
G01M 15/14 - Testing gas-turbine engines or jet-propulsion engines
F01D 21/00 - Shutting-down of machines or engines, e.g. in emergencyRegulating, controlling, or safety means not otherwise provided for
F01D 21/12 - Shutting-down of machines or engines, e.g. in emergencyRegulating, controlling, or safety means not otherwise provided for responsive to temperature
G01K 1/02 - Means for indicating or recording specially adapted for thermometers
22.
METHOD FOR REDUCING DAMAGE TO COMPONENTS OF GAS TURBINE ENGINES
A method for reducing damage to a component of a gas turbine engine includes: determining one or more atmospheric agents that are predicted to be ingested by the gas turbine engine during operation and their concentration; determining a composition and an amount of a predicted deposit that is predicted to form on the component based on the concentration of the one or more atmospheric agents; determining a predicted damage to the component based at least on the composition and the amount of the predicted deposit, and a composition of a coating of the component; determining an additive and its concentration based on the composition and the amount of the predicted deposit and the predicted damage, such that the additive changes at least one of thermochemical and thermomechanical properties of the predicted deposit to reduce the predicted damage to the component; and applying, in-situ, the additive to the component.
Combustion equipment for a gas turbine engine includes an annular cowl positioned upstream of a head plate. In a longitudinal plane which includes a central axis and which lies azimuthally between adjacent fuel injectors of the combustion equipment, the annular cowl has a profile which extends along a local cowl axis and which is non-symmetric with respect to the local cowl axis.
An electrical power system 10 and a method 300 of controlling an electrical power system 10 are provided. The electrical power system 10 comprises a DC:DC power converter 100 connected between a DC power source 11 and a DC electrical network 12. The DC electrical network 12 comprises at least a first zone Z1 for powering a first group of one or more electrical loads 12La-b, a second zone Z2 for powering a second group of one or more electrical loads 12Lc-d, a first controllable circuit breaker X1, and a second controllable circuit breaker X2. The electrical power system 10 further comprises a control system 150 configured to: in response to determining there is a fault in the DC electrical network 12: control a switching operation of a plurality of transistors of the DC:DC power converter 100 to supply a controlled and gradually increasing amount of current from the DC power source 11 to the DC electrical network 12; open the first controllable circuit breaker X1 if the gradually increasing amount of current supplied to the DC electrical network 12 reaches a level defined by a first trip profile 201, the first trip profile 201 defining a gradually decreasing current level; and open the second controllable circuit X2 breaker if the gradually increasing amount of current supplied to the DC electrical network 12 reaches a level defined by a second trip profile 202, the second trip profile 202 defining a gradually decreasing current level, the gradually decreasing current level defined by the first trip profile 201 being higher than the gradually decreasing current level defined by the second trip profile 202.
H02M 1/32 - Means for protecting converters other than by automatic disconnection
B60R 16/03 - Electric or fluid circuits specially adapted for vehicles and not otherwise provided forArrangement of elements of electric or fluid circuits specially adapted for vehicles and not otherwise provided for electric for supply of electrical power to vehicle subsystems
H02M 3/335 - Conversion of DC power input into DC power output with intermediate conversion into AC by static converters using discharge tubes with control electrode or semiconductor devices with control electrode to produce the intermediate AC using devices of a triode or a transistor type requiring continuous application of a control signal using semiconductor devices only
A computer implemented method of modelling the degradation of at least a component within an abrasive environment, the method comprising: obtaining a 3D scan of a surface of a component, processing the surface images of the component, determining the surface properties, inputting the data into a trained prediction model, predicting the performance of the component, and simulating the surface evolution over time or use of the component.
A compressor assembly for a gas turbine engine includes a shroud assembly, an outer case assembly, and a plurality of locating bolt assemblies. The shroud assembly extends circumferentially around the engine axis. The outer case assembly includes an outer case that extends circumferentially around the axis and a plurality of fasteners that couple the shroud assembly with the outer case. The plurality of locating bolt assemblies extend into the outer case and abut the shroud assembly at a predetermined axial location to axially locate the shroud assembly.
A compressor assembly for a gas turbine engine comprising an outer case, a shroud arranged circumferentially around the axis to direct compressed air through an impeller, and an actuator coupled with the outer case and the shroud to vary the position of the shroud axially relative to the outer case. The actuator includes a mount arm, an actuator body, and a travel stop. The mount arm is coupled with the outer case. The actuator body is coupled with the mount arm and the shroud to control axial movement of the shroud relative to the outer case. The travel stop is coupled to the mount arm and extends away from the mound arm and is configured to limit a forward most axial position of the shroud relative to the outer case.
F01D 11/22 - Actively adjusting tip-clearance by mechanically actuating the stator or rotor components, e.g. moving shroud sections relative to the rotor
28.
APPARATUS FOR SUPPORTING AT LEAST A PART OF AN ENGINE
Apparatus for supporting at least a part of an engine, the engine comprising: an engine stand configured to support at least a part of an engine; an accelerometer coupled to the engine stand and configured to: measure acceleration of the engine stand, and generate accelerometer data; and a first processor configured to receive the accelerometer data from the accelerometer.
A method for optimizing a manufacturing process includes arranging a finite element method simulation model, a microstructure model, and a material model in a closed loop. The method includes performing an iterative simulation process to determine a simulated output of the manufacturing process. The iterative simulation process includes performing a plurality of iterations. Each of the plurality of iterations includes the steps of: determining, by the finite element method simulation model, a plurality of thermomechanical parameters based on a plurality of process parameters and a plurality of previous predicted material properties; determining, by the microstructure model, a predicted change in a microstructure based on the plurality of thermomechanical parameters; and determining, by the material model, a plurality of current predicted material properties based on the predicted change in the microstructure.
G05B 19/418 - Total factory control, i.e. centrally controlling a plurality of machines, e.g. direct or distributed numerical control [DNC], flexible manufacturing systems [FMS], integrated manufacturing systems [IMS] or computer integrated manufacturing [CIM]
An impellor assembly for a liquid hydrogen pump. The assembly comprises a shaft, one or more impellors mounted to the shaft, a fastener configured to engage with the shaft at a first engagement point and with the one or more impellor at a second engagement point to axially clamp the one or more impellor to the shaft, an axially unconstrained length of the fastener being defined by an axial distance between the first and second engagement points. An axial extent of a clamped portion of the one or more impellors corresponds to the axially unconstrained length of the fastener. The fastener and the impellor comprise a material having a first coefficient of thermal expansion and the shaft comprises a material having a second coefficient of thermal expansion, wherein the first and second coefficients of thermal expansion are different.
A turbofan gas turbine engine comprises, in axial flow sequence, a heat exchanger module, a fan assembly, a compressor module, a turbine module, and an exhaust module. The fan assembly comprises a plurality of fan blades defining a fan diameter (D). The heat exchanger module is in fluid communication with the fan assembly by an inlet duct, and the heat exchanger module comprises a plurality of radially-extending hollow vanes arranged in a circumferential array with a channel extending axially between each pair of adjacent hollow vanes. The heat exchanger module has a square axial cross-sectional profile, where a side length of the square cross-section is D.
F02C 7/14 - Cooling of plants of fluids in the plant
F02C 7/18 - Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
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
A gas turbine engine for an aircraft includes a fan system having a reverse travelling wave first flap mode, Fan RTW, and including a fan located upstream of the engine core; a fan shaft; and a front engine structure arranged to support the fan shaft and having a front engine structure nodding mode comprising a pair of modes at similar, but not equal, natural frequencies in orthogonal directions; and a gearbox. An LP rotor system including the fan system and a gearbox output shaft arranged to drive the fan shaft has a first reverse whirl rotor dynamic mode, Rotor RW, and a first forward whirl rotor dynamic mode, 1FW. The engine has a maximum take-off speed, MTO. A backward whirl frequency margin of:
A gas turbine engine for an aircraft includes a fan system having a reverse travelling wave first flap mode, Fan RTW, and including a fan located upstream of the engine core; a fan shaft; and a front engine structure arranged to support the fan shaft and having a front engine structure nodding mode comprising a pair of modes at similar, but not equal, natural frequencies in orthogonal directions; and a gearbox. An LP rotor system including the fan system and a gearbox output shaft arranged to drive the fan shaft has a first reverse whirl rotor dynamic mode, Rotor RW, and a first forward whirl rotor dynamic mode, 1FW. The engine has a maximum take-off speed, MTO. A backward whirl frequency margin of:
the
lowest
frequency
of
either
mode
Fan
RTW
or
Rotor
RW
at
the
MTO
speed
the
MTO
speed
A gas turbine engine for an aircraft includes a fan system having a reverse travelling wave first flap mode, Fan RTW, and including a fan located upstream of the engine core; a fan shaft; and a front engine structure arranged to support the fan shaft and having a front engine structure nodding mode comprising a pair of modes at similar, but not equal, natural frequencies in orthogonal directions; and a gearbox. An LP rotor system including the fan system and a gearbox output shaft arranged to drive the fan shaft has a first reverse whirl rotor dynamic mode, Rotor RW, and a first forward whirl rotor dynamic mode, 1FW. The engine has a maximum take-off speed, MTO. A backward whirl frequency margin of:
the
lowest
frequency
of
either
mode
Fan
RTW
or
Rotor
RW
at
the
MTO
speed
the
MTO
speed
may be in the range from 15 to 50%.
F02C 7/36 - Power transmission between the different shafts of the gas-turbine plant, or between the gas-turbine plant and the power user
B64D 27/10 - Aircraft characterised by the type or position of power plants of gas-turbine type
F02C 3/073 - 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 the compressor and turbine stages being concentric
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
F04D 25/02 - Units comprising pumps and their driving means
A turbine shroud assembly includes a first shroud segment, a second shroud segment, and a plurality of seals. The first shroud segment includes a first carrier segment arranged circumferentially at least partway around a central axis and a first blade track segment supported by the first carrier segment. The second shroud segment is arranged circumferentially adjacent the first shroud segment about the central axis. The plurality of seals extend circumferentially into the first shroud segment and the second shroud segment to block gases from escaping the gas path radially between the first shroud segment and the second shroud segment.
A propulsion system comprises a propulsive hydrogen-burning gas turbine engine, a fuel cell stack auxiliary power unit (APU) and a first tank arranged to store liquid hydrogen with an ullage. A first fuel line includes a first pump and a first vaporiser and transports hydrogen from the first tank to combustion apparatus of the engine during operation of the propulsion system. A second fuel line includes a second fuel pump and a second vaporiser and transports hydrogen from the first tank to the fuel cell stack APU. A duct connects the second fuel line at a position thereon between the second vaporiser and the fuel cell stack to the ullage of the first tank, providing for pressure in the first tank to be maintained therein as liquid hydrogen within the first tank is depleted, thus avoiding cavitation of liquid hydrogen within the first fuel pump.
F02C 3/22 - Gas-turbine plants characterised by the use of combustion products as the working fluid using a special fuel, oxidant, or dilution fluid to generate the combustion products the fuel or oxidant being gaseous at standard temperature and pressure
F02C 7/08 - Heating air supply before combustion, e.g. by exhaust gases
35.
POLISHING SYSTEM AND METHOD OF POLISHING A COMPONENT
A polishing system for polishing a component has a polishing device that has a housing, a polishing tool, and at least one pressure applicator configured to apply a pressure on the polishing tool to engage the polishing tool with the component. The polishing system further includes a holder to position the polishing device relative to the component and a controller configured to transmit a control signal to the at least one pressure applicator to apply a predetermined amount of pressure on the polishing tool. The polishing device further includes a pressure sensor configured to generate a pressure signal indicative of an amount of pressure being applied by the at least one pressure applicator and the holder. The polishing system further includes a component monitoring device that is configured to generate a process signal indicative of a material removal rate from the component.
B24B 49/04 - Measuring or gauging equipment for controlling the feed movement of the grinding tool or workArrangements of indicating or measuring equipment, e.g. for indicating the start of the grinding operation according to the instantaneous size and required size of the workpiece acted upon, the measuring or gauging being continuous or intermittent involving measurement of the workpiece at the place of grinding during grinding operation
B24B 49/12 - Measuring or gauging equipment for controlling the feed movement of the grinding tool or workArrangements of indicating or measuring equipment, e.g. for indicating the start of the grinding operation involving optical means
B24B 49/18 - Measuring or gauging equipment for controlling the feed movement of the grinding tool or workArrangements of indicating or measuring equipment, e.g. for indicating the start of the grinding operation taking regard of the presence of dressing tools
36.
GAS TURBINE ENGINE WITH AN IMPROVED THERMAL MANAGEMENT SYSTEM
A gas turbine engine with a heat management system configured to provide lubrication and cooling to a power gearbox and turbomachinery bearings, the heat management system having at least one air-lubricant heat exchanger configured to dissipate to a first heat sink, and at least one fuel-lubricant heat exchanger configured to dissipate to a second heat sink. The first heat sink being air and the second heat sink being fuel. A first proportion of heat generated by the power gearbox and the turbomachinery and dissipated to air is defined as
A gas turbine engine with a heat management system configured to provide lubrication and cooling to a power gearbox and turbomachinery bearings, the heat management system having at least one air-lubricant heat exchanger configured to dissipate to a first heat sink, and at least one fuel-lubricant heat exchanger configured to dissipate to a second heat sink. The first heat sink being air and the second heat sink being fuel. A first proportion of heat generated by the power gearbox and the turbomachinery and dissipated to air is defined as
(
first
amount
of
heat
first
amount
of
heat
+
second
amount
of
heat
)
85
%
MTO
at 85% of a core shaft maximum take-off speed, and
the at least one air-lubricant heat exchanger and the at least one fuel-lubricant heat exchanger are configured to provide the first proportion in the range of from 0.30 to 0.70.
A printed circuit board assembly includes a printed circuit board having an upper side and a lower side, an electrical module having an upper side and a lower side, and a holding down construction. The upper side of the electrical module is arranged on the lower side of the printed circuit board. The holding down construction includes screwing posts that are configured to be screwed against the printed circuit board. The holding down construction is arranged on the upper side of the printed circuit board and includes contact structures that are at a distance from the screwing posts and configured to rest or press on the printed circuit board at specific contact points only. The printed circuit board includes dedicated support points that correspond to the specific contact points of the holding down construction and are contacted by the specific contact points. The dedicated support points are mechanically reinforced.
A propulsion system comprises a propulsive hydrogen-burning gas turbine engine, a first tank storing liquid hydrogen with an ullage and a first fuel line including a fuel pump and a vaporiser, the first fuel line providing gaseous hydrogen to the engine during operation of the system. A second tank storing gaseous hydrogen is coupled by a second fuel line to the first fuel line at a position thereon between the vaporiser and the engine, providing for engine start-up (when the vaporiser is inoperative) and power-boosting during operation of the system. A duct connects gaseous hydrogen within the second tank to the ullage in the first tank in order maintain pressure in the first tank as liquid hydrogen within it is depleted, preventing cavitation of liquid hydrogen within the fuel pump.
Rolls-Royce North American Technologies, Inc. (USA)
Rolls-Royce plc (United Kingdom)
Inventor
Schenk, Peter
Tanner, Mark Angelo
Abstract
An example system includes an electrical machine electrically configured to generate electrical energy used by one or more components of a gas-turbine engine; an energy storage system; and a controller electrically connected to the energy storage system and configured to receive electrical energy from the energy storage system, wherein, in response to the gas-turbine engine being shut off, the controller is configured to cause the electrical machine to rotate a rotor of the gas-turbine engine using the energy received from the energy storage system.
B64D 31/00 - Power plant control systemsArrangement of power plant control systems in aircraft
B60L 50/52 - Electric propulsion with power supplied within the vehicle using propulsion power supplied by batteries or fuel cells characterised by DC-motors
B64D 27/02 - Aircraft characterised by the type or position of power plants
B64D 27/10 - Aircraft characterised by the type or position of power plants of gas-turbine type
B64D 27/24 - Aircraft characterised by the type or position of power plants using steam or spring force
H02J 7/00 - Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries
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
H02K 7/18 - Structural association of electric generators with mechanical driving motors, e.g.with turbines
H02K 11/33 - Drive circuits, e.g. power electronics
A bearing carrier support for connecting a rotary shaft of a gas turbine engine to a static portion of the gas turbine engine. The bearing carrier support has: a bearing portion for supporting the rotary shaft; a flange portion for attaching the bearing carrier support to the static portion of the gas turbine engine; and a support portion that connects the flange portion and the bearing portion. The support portion has a plurality of circumferentially distributed struts that are axially aligned with respect to the rotary shaft. A snubber extends from either the flange portion or bearing portion to form an abutment face.
The invention relates to a printed circuit board assembly having: a printed circuit board (1) which has a topside (11) and an underside (12), at least one electrical module (2) which has a topside (21) and an underside (22) and is arranged with its topside (21) against the underside (12) of the printed circuit board (1), and a heat sink (3) against which the underside (22) of the electrical module (2) rests via a heat-conducting material (4). The underside (22) of the electrical module (2) has a height profile (25), and a gap (5), in which the heat-conducting material (4) is arranged, is formed between the topside (31) of the heat sink (3) and the underside (22) of the electrical module (2). According to the invention, the heat sink (3) is structured in the area of its surface (31) in which the electrical module (2) rests with its underside (22) via the heat conducting material (4), and the structuring (35) compensates the height profile (25) of the underside (22) of the electrical module (2), such that the gap (5) is of constant height. The invention further relates to a method for producing such a printed circuit board assembly.
A fault detector for a control system that includes a controller, a solenoid driver, a current sensor and a solenoid. The solenoid driver provides a current to the solenoid in response to a control signal provided by the controller to the solenoid driver and the current sensor measures the current provided by the solenoid driver to the solenoid to determine a current measurement. At any moment, the control signal corresponds to one of a demanded zero current, a demanded first current magnitude or a demanded second current magnitude. The fault detector detects a fault based upon a comparison of the current measurement to an expected current range, wherein the expected current range is dependent upon which of the demanded zero current, demanded first current magnitude or the demanded second current magnitude the control system corresponds to at that moment.
F16K 37/00 - Special means in or on valves or other cut-off apparatus for indicating or recording operation thereof, or for enabling an alarm to be given
A fuel system for a hydrogen fueled aircraft propulsion system comprises a tank configured to store hydrogen, a first inductor provided within the tank and configured to heat hydrogen fuel within the tank, and a second inductor provided externally to the tank, and configured to induce a current in the first inductor.
A combustion chamber assembly for an engine includes a combustion chamber defining a combustion space delineated by a combustion chamber wall and extending in a main flow direction from a combustion chamber head to a combustion chamber outlet. A fuel injection system is joined to the wall at the combustion chamber head and has a fuel feed for fuel and a nozzle head for injecting the fuel into the combustion space. The wall also has an integrated heat exchanger duct via which the fuel is routed within a first duct section of the heat exchanger duct which is connected to the fuel line from the combustion chamber head in the direction of the combustion chamber outlet and, after flowing through a deflection region, in a second duct section of the heat exchanger duct, back in the direction of the combustion chamber head and of the nozzle head.
A rotary assembly of a pressurized air system for an aircraft with a rotor configured to be mechanically coupled to a spool of a gas turbine engine and a flow modifier with a first section and a second section. The first section defining a plurality of first flow channels configured to receive flow from the rotor. The second section defining a plurality of second flow channels configured to direct flow towards the rotor. The rotary assembly is configured to permit relative movement between the rotor and the flow modifier to move between a turbine configuration in which the rotor is configured to receive air from an external air source to drive the spool to rotate and a compressor configuration in which the rotor is configured to be driven to rotate by the spool and to receive and compress air from the gas turbine engine.
B64D 13/02 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being pressurised
F02C 6/06 - Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output providing compressed gas
A battery pack module, for example, is used in an electric or hybrid aircraft. A battery pack module includes: a plurality of battery cells arranged in a battery cell array; a battery management system electrically connected to the battery cell array; an enclosure surrounding the battery cell array; a vent connected to the enclosure and arranged to provide a fluid flow path between an interior of the enclosure and an external environment; a disc arranged to provide a fluid seal between the interior of the enclosure and the vent, the disc configured to rupture upon a pressure differential between the interior of the enclosure and the external environment exceeding a predetermined threshold; and a sensing circuit connected between the disc and the battery management system and configured to provide a signal to the battery management system upon rupture of the disc.
H01M 10/42 - Methods or arrangements for servicing or maintenance of secondary cells or secondary half-cells
B64D 27/357 - Arrangements for on-board electric energy production, distribution, recovery or storage using batteries
H01M 10/48 - Accumulators combined with arrangements for measuring, testing or indicating the condition of cells, e.g. the level or density of the electrolyte
H01M 50/204 - Racks, modules or packs for multiple batteries or multiple cells
A method of operating a laser additive manufacturing machine includes manufacturing at least one first fluid-flow coupon, that includes a plate defining a plurality of holes, at a corresponding beam offset value of the laser additive manufacturing machine. The method further includes disposing the at least one first fluid-flow coupon in a testing rig, directing a fluid flow towards the at least one first fluid-flow coupon, measuring a fluid flow rate through the at least one first fluid-flow coupon, determining a calibration curve by correlating a beam offset of the laser additive manufacturing machine with a flow parameter based on the fluid flow rate through the at least one first fluid-flow coupon and the corresponding beam offset value, determining a target beam offset value corresponding to a target flow value of the flow parameter, and calibrating and operating the laser additive manufacturing machine using the target beam offset value.
B29C 64/393 - Data acquisition or data processing for additive manufacturing for controlling or regulating additive manufacturing processes
B22F 10/28 - Powder bed fusion, e.g. selective laser melting [SLM] or electron beam melting [EBM]
B22F 10/31 - Calibration of process steps or apparatus settings, e.g. before or during manufacturing
B28B 1/00 - Producing shaped articles from the material
B28B 17/00 - Details of, or accessories for, apparatus for shaping the materialAuxiliary measures taken in connection with such shaping
B29C 64/153 - Processes of additive manufacturing using only solid materials using layers of powder being selectively joined, e.g. by selective laser sintering or melting
The disclosure relates to a battery pack module, for example for use in an electric or hybrid aircraft. Example embodiments include a battery pack module (600) comprising: a plurality of battery cells (6011-n) arranged in a battery cell array (602); an enclosure (604) comprising a plurality of walls surrounding the battery cell array (602); and a vent (605) connected to the enclosure (604) and arranged to provide a fluid flow path between an interior (607) of the enclosure (604) and an external environment (610) upon a pressure differential between the interior (607) of the enclosure (604) and the external environment (610) exceeding a predetermined threshold, wherein the walls of the enclosure (604) are composed of a fire-resistant laminated material comprising a plurality of fabric layers.
H01M 50/231 - MountingsSecondary casings or framesRacks, modules or packsSuspension devicesShock absorbersTransport or carrying devicesHolders characterised by the material of the casings or racks having a layered structure
H01M 10/658 - Means for temperature control structurally associated with the cells by thermal insulation or shielding
H01M 50/249 - MountingsSecondary casings or framesRacks, modules or packsSuspension devicesShock absorbersTransport or carrying devicesHolders specially adapted for aircraft or vehicles, e.g. cars or trains
The disclosure relates to electrical machine condition monitoring by placement of a Fibre Bragg Grating (FBG) in the stator of an electrical machine. Example embodiments include an electrical machine comprising: a stator having a plurality of stator teeth having windings around each tooth; a rotor rotatably mounted within the stator; and an optical fibre mounted to the stator, wherein the optical fibre comprises a Fibre Bragg Grating, FBG, positioned between an adjacent pair of stator teeth and oriented to measure a tangential strain between the pair of stator teeth.
H02K 11/20 - Structural association of dynamo-electric machines with electric components or with devices for shielding, monitoring or protection for measuring, monitoring, testing, protecting or switching
A guide vane assembly includes a guide vane and a sealing assembly slidable along a span of the guide vane relative to the guide vane and extending along a chordal axis and the span of the guide vane. The sealing assembly includes a plate configured to be disposed around at least a portion of an external surface of the guide vane. The sealing assembly further includes a manifold coupled to the plate and configured to receive pressurized fluid therein. The manifold is disposed around the plate. The sealing assembly further includes a plurality of flow tubes extending between the manifold and the plate. Each of the plurality of flow tubes are configured to receive the pressurized fluid from the manifold.
Embodiments described herein relate to methods and apparatuses for performing classification of a classification subject. A computer implemented method for initiating use of one or more classifier models to perform classification of a classification subject into one of a plurality of classes comprises: for each of a plurality of classifier models, obtaining respective classifier confusion information, wherein the classifier confusion information indicates, for each actual class in the plurality of classes, the likelihood of the classifier model classifying the actual class as each predicted class in the plurality of classes; obtaining risk confusion information indicating a risk associated with each actual class and predicted class pair; for each of the plurality of classifier models, determining a respective risk metric from the respective classifier confusion information and the risk confusion information; and initiating use of one or more of the plurality of classifier models based on the respective risk metrics.
An electrical power system includes: an H-bridge DC:DC power converter including first and second half-bridge circuits having low-side transistors and a high-side transistors, and an inductor connected between AC sides of the first and second half-bridge circuits; a DC power source connected to a first half-bridge circuit DC side; a DC electrical network connected to a second half-bridge circuit DC side; and a control system. The control system: controls the low-side and high-side transistors' switching state of the first and second half-bridge circuits; monitors one or more electrical power system operating parameters and determines whether there is a fault in the DC electrical network; and in response, modifies a switching operation of the low-side and high-side transistors of the first and second half-bridge circuits to supply a controlled amount of current from the DC power source to the DC electrical network.
H02M 1/32 - Means for protecting converters other than by automatic disconnection
H02M 3/156 - Conversion of DC power input into DC power output without intermediate conversion into AC by static converters using discharge tubes with control electrode or semiconductor devices with control electrode using devices of a triode or transistor type requiring continuous application of a control signal using semiconductor devices only with automatic control of output voltage or current, e.g. switching regulators
53.
Turbine assembly with confronting vane and turbine shroud segment
A turbine assembly adapted for use with a gas turbine engine includes a turbine shroud assembly and a turbine vane. The turbine shroud assembly includes a carrier segment arranged circumferentially at least partway around an axis and a blade track segment supported by the carrier segment to locate the blade track segment radially outward of the axis. The turbine vane is located axially forward of the turbine shroud assembly and cooperates with the turbine shroud assembly to form a tortuous flow path therebetween.
A turbine assembly includes a turbine case, a vane assembly, and a locating plate. The vane assembly includes a first vane and an outer platform arranged on a radially outer end of the first vane, the outer platform including a first anti-rotation protrusion extending radially outwardly away from a radially outwardly-facing surface of the outer platform. The locating plate is radially outside of the vane assembly and includes a main wall and two anti-rotation extensions extending radially inwardly. The first anti-rotation protrusion of the vane assembly is arranged to engage with one of the anti-rotation extensions so as to block circumferential movement of the vane assembly relative to the locating plate.
Disclosed is a computer-implemented method for controlling an engine system of a vehicle comprising: determining an operating condition of the vehicle; determining one or more contextual conditions relevant to the vehicle; selecting, based upon both the determined operating condition and the determined one or more contextual conditions, a control profile for the engine system from a directory comprising a plurality of control profiles having different control characteristics; applying the selected control profile to a controller of the engine system; and controlling the engine system with the controller in accordance with the selected control profile. Also disclosed are an engine control system, a gas turbine engine, and an aircraft.
Rolls-Royce North American Technologies Inc. (USA)
Rolls-Royce Corporation (USA)
Inventor
Heeter, Robert W.
Rivers, Jonathan M.
Molnar, Jr., Daniel E.
Abstract
A fan case assembly adapted for use with a gas turbine engine includes a fan casing and a bleed air flow control system. The fan casing includes an annular case and a fan track liner coupled with the annular case. The bleed air flow control system is configured to bleed selectively a portion of air flowing through a gas path of the fan case assembly for use as a cooling source in the fan case assembly.
F02C 7/18 - Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
F02C 9/18 - Control of working fluid flow by bleeding, by-passing or acting on variable working fluid interconnections between turbines or compressors or their stages
F04D 29/52 - CasingsConnections for working fluid for axial pumps
F04D 29/58 - CoolingHeatingDiminishing heat transfer
57.
Adjustable fan track liner with groove array active fan tip treatment for distortion tolerance
Rolls-Royce North American Technologies Inc. (USA)
Rolls-Royce Corporation (USA)
Inventor
Molnar, Jr., Daniel E.
Heeter, Robert W.
Rivers, Jonathan M.
Abstract
A gas turbine engine includes a fan and a fan case assembly. The fan includes a fan rotor configured to rotate about an axis of the gas turbine engine and a plurality of fan blades coupled to the fan rotor for rotation therewith. The fan case assembly extends circumferentially around the plurality of fan blades radially outward of the plurality of the fan blades.
F01D 11/08 - Preventing or minimising internal leakage of working fluid, e.g. between stages for sealing space between rotor blade tips and stator
F01D 11/22 - Actively adjusting tip-clearance by mechanically actuating the stator or rotor components, e.g. moving shroud sections relative to the rotor
F04D 29/52 - CasingsConnections for working fluid for axial pumps
A gas turbine engine for an aircraft comprising an engine core comprising a turbine, a compressor, and a core shaft connecting the turbine to the compressor. A fan located upstream of the engine core, the fan comprising a plurality of fan blades and having a fan diameter and a gearbox arranged to receive an input from the core shaft and to output drive to the fan so as to drive the fan at a lower rotational speed than the core shaft, thereby defining a gear ratio. The gearbox being an epicyclic gearbox. A gearbox diameter is defined as the pitch circle diameter of the ring gear; and a geared-fan value defined by a product of the fan diameter and gear ratio, which are divided by the gearbox diameter, being greater than 12.
The invention relates to an electric machine (1; 1′), comprising: a stator (10); a rotor (11) that can be rotated relative to the stator (10); a shaft (12) that can be rotated relative to the stator (10); and a flexible coupling element (13; 13′; 13″) having a first connecting section (130; 130′) fixed to the rotor (11) and a second connecting section (131; 131′; 131″) fixed to the shaft (12). which connecting sections have different diameters (D1, D2) and are connected to one another via an alternately curved connecting surface (132; 132′).
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
B64D 27/30 - Aircraft characterised by electric power plants
F16D 3/76 - Yielding couplings, i.e. with means permitting movement between the connected parts during the drive with the coupling parts connected by one or more intermediate members shaped as an elastic ring centered on the axis, surrounding a portion of one coupling part and surrounded by a sleeve of the other coupling part
60.
METHOD FOR PRODUCING A COMPONENT OF AN ELECTRIC MACHINE, COMPONENT OF AN ELECTRIC MACHINE, AND ELECTRIC MOTOR IN AN AIRCRAFT PROPULSION SYSTEM INCLUDING A COMPONENT OF THIS TYPE
The invention relates to a method for producing a component (10) of an electric machine, wherein at least one permanent magnet means (1) of the component (10) is arranged on or at the component (10), together with at least one mechanical restraining means (2) for spatially fixing the at least one permanent magnet means (1), and the at least one mechanical restraining means (2) consists of a composite material or contains same, characterised in that, at least during a thermal treatment of the component (10), a means (3, F) is used for the targeted control of the magnetic field of the permanent magnet means (1).
H01F 13/00 - Apparatus or processes for magnetising or demagnetising
H02K 1/02 - Details of the magnetic circuit characterised by the magnetic material
H02K 15/035 - Processes or apparatus specially adapted for manufacturing, assembling, maintaining or repairing of dynamo-electric machines of stator or rotor bodies having permanent magnets on the rotor
H02K 15/121 - Impregnating, moulding insulation, heating or drying of windings, stators, rotors or machines of cores
A method of operating a gas turbine engine including: an engine core with a turbine, compressor, a fuel combustor, and a core shaft connecting the turbine to the compressor; a fan; a gearbox that receives an input from the core shaft and outputs drive to the fan; an oil loop system arranged to supply oil to the gearbox; and a heat exchange system including: an air-oil heat exchanger through which the oil flows; a fuel-oil heat exchanger through which the oil and the fuel flow; a temperature sensor downstream of the fuel-oil heat exchanger; and a valve arranged to allow oil or air flow rate through at least one heat exchanger to be varied, the method including: determining if the fuel temperature has increased above a set threshold at cruise conditions; and in response, controlling the valve so as to change the flow rate through the heat exchanger.
A DC:DC converter includes: a DC:AC converter circuit having DC and AC sides; an AC:DC converter circuit having DC and sides; an AC link connecting the AC side of the DC:AC circuit and the AC side of the AC:DC converter circuit, the AC link including a transformer having a first winding connected to the AC side of the DC:AC converter circuit and a second winding connected to the AC side of the AC:DC converter; a capacitor; and a switch arrangement having a first state and a second state, wherein: in the first state, the capacitor is connected in series between the AC side of the DC:AC converter circuit and the first winding of the transformer; and in the second state, there is a current path between the AC side of the DC:AC converter circuit and the first winding of the transformer that does not include the capacitor.
H02M 3/335 - Conversion of DC power input into DC power output with intermediate conversion into AC by static converters using discharge tubes with control electrode or semiconductor devices with control electrode to produce the intermediate AC using devices of a triode or a transistor type requiring continuous application of a control signal using semiconductor devices only
A DC:DC power electronics converter in an electrical power system includes: DC:AC and AC:DC converters; and an AC link connecting AC sides of the converters, the AC link including a transformer having first and second windings connected respectively to AC sides of the converters; a DC power source connected to the DC side of the DC:AC converter; a DC electrical network connected to the DC side of the AC:DC converter; and a control system to: control a switching operation of respective first and second pluralities of transistors of the converters, monitor one or more operating parameters of the electrical power system and determine whether there is a fault in the electrical network, and if so, modify a switching operation of the first and/or second plurality of transistors to supply a controlled amount of fault current from the DC power source to the electrical network via the DC:DC power electronics converter.
H02H 7/12 - Emergency protective circuit arrangements specially adapted for specific types of electric machines or apparatus or for sectionalised protection of cable or line systems, and effecting automatic switching in the event of an undesired change from normal working conditions for convertersEmergency protective circuit arrangements specially adapted for specific types of electric machines or apparatus or for sectionalised protection of cable or line systems, and effecting automatic switching in the event of an undesired change from normal working conditions for rectifiers for static converters or rectifiers
H02M 3/335 - Conversion of DC power input into DC power output with intermediate conversion into AC by static converters using discharge tubes with control electrode or semiconductor devices with control electrode to produce the intermediate AC using devices of a triode or a transistor type requiring continuous application of a control signal using semiconductor devices only
65.
SYSTEM FOR COOLING COMPONENTS ASSOCIATED WITH GAS TURBINE ENGINE
A system for cooling one or more components associated with a gas turbine engine includes a main duct, a first duct that receives and directs a portion of airflow from the main duct towards a core zone cooling arrangement of the gas turbine engine, and a second duct that receives and directs a portion of the airflow from the main duct towards a turbine case cooling arrangement or an oil cooling unit of the gas turbine engine. The system includes a valve unit including a first valve member disposed in the first duct and a second valve member disposed in the second duct. The first and second valve members control a fluid flow through the first and second ducts, respectively. The system includes at least one controller configured to control the valve unit to modulate the portion of the airflow through each of the first and second ducts.
A power distribution system includes a plurality of energy supply systems, a plurality of first electric propulsion units, and a second electric propulsion unit different from the plurality of first electric propulsion units. Each energy supply system is configured to power at least two of the first electric propulsion units and each first electric propulsion unit is configured to be powered by at least two of the energy supply systems. Further, at least a subset of the energy supply systems is configured to power the second electric propulsion unit.
B64D 35/04 - Transmitting power from power plants to propellers or rotorsArrangements of transmissions characterised by the transmission driving a plurality of propellers or rotors
B64C 29/00 - Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
B64D 35/02 - Transmitting power from power plants to propellers or rotorsArrangements of transmissions specially adapted for specific power plants
67.
AIRCRAFT WING COMPRISING A STORAGE TANK FOR GASEOUS HYDROGEN
A storage tank for gaseous hydrogen includes a continuous tank wall defining a serial array of hollow elongate tank portions of substantially constant cross-section and hollow connecting portions defining an internal storage volume, wherein adjacent ends of any pair of adjacent hollow elongate tank portions are connected by a hollow connecting portion having a cross-sectional dimension smaller than those of the adjacent hollow elongate tanks portions. The tank may be included in an aircraft wing such that it extends spanwise through one or more internal spars of the wing, thus providing a continuous gas storage volume at a given chordwise position notwithstanding the spars, and providing for storage of gaseous hydrogen at higher gravimetric efficiency than is achievable by a plurality of coupled discrete tanks disposed between the spars.
A method for controlling a power beam process includes carrying out a plurality of test power beam processes using a power beam on one or more test components and determining a plurality of power distributions corresponding to the plurality of test power beam processes. The method includes determining a plurality of beam parameters, generating derived features based on the plurality of beam parameters, and determining a plurality of process characteristics of each test power beam process. The method further includes generating a comprehensive dataset, dividing the comprehensive dataset into a test dataset and a training dataset, and determining a plurality of key discriminative features from the plurality of derived features of a set of training power distributions of the training dataset.
G05B 19/4155 - 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 programme execution, i.e. part programme or machine function execution, e.g. selection of a programme
A battery charging system including a battery enclosure defining an interior space containing a battery storage medium, the interior space configured to house one or more battery cells; a charging terminal electrically coupled to the one or more battery cells and configured to receive electrical power from a power source to charge one or more battery cells; wherein the interior space is configured to be coupled to a pressurising device for applying pressure to the battery storage medium in the interior space; and wherein during charging of the one or more battery cells, the battery storage medium in the interior space is pressurised to cause an isostatic pressure to be applied to the one or more battery cells. A method of charging of charging one or more battery cells provided.
H01M 10/637 - Control systems characterised by the use of reversible temperature-sensitive devices, e.g. NTC, PTC or bimetal devicesControl systems characterised by control of the internal current flowing through the cells, e.g. by switching
A combustor assembly (16) for a gas turbine having an annular combustor body and an annular combustor rear. The combustor body and the combustor rear are connected by: i) fit between a radially outer surface of the radially outer wall of the combustor rear and a radially inner surface of the radially outer wall of the combustor body, ii) fit between a radially inner surface of the radially inner wall of the combustor rear and a radially outer surface of the radially inner wall of the combustor body, and iii) one or more retention pins extending radially through respective apertures in the combustor body and in the combustor rear. The combustor rear tapers towards the engine axis as it extends rearwardly.
F23R 3/00 - Continuous combustion chambers using liquid or gaseous fuel
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
Computer implementations for managing contract data requirements list (CDRL) deliverables are disclosed. In some implementations, a controller identifies a CDRL deliverable associated with a program. The controller determines whether the CDRL deliverable is associated with a milestone of a plurality of milestones associated with the program and whether the CDRL is associated with a recurrence. In addition, the controller determines a delivery date for the CDRL deliverable based on whether the CDRL is associated with the milestone and whether the CDRL deliverable is associated with the recurrence. The controller displays, via a display, a CDRL deliverable name of the CDRL deliverable and at least one of: the delivery date, a delivery status corresponding to the delivery date, and a delivery evaluation corresponding to the delivery date.
A method for controlling a drive system (1, 1') of an aircraft (2, 2'), comprising the following steps carried out by a control system (12) of the drive system (1, 1'): detecting (S10) at least one parameter which describes the operation of the drive system (1, 1'), and detecting at least one blade position of at least one blade (103, 210) of the aircraft (2, 2'); determining (S11) an operating state of the aircraft (2) using the at least one detected parameter and the at least one detected blade position; and operating (S12) at least one electric drive unit (10) of the drive system (1, 1') on the basis of a maximum value, predefined for the determined operating state, of a thrust and/or a power output of the at least one electric drive unit (10) of the drive system (1, 1').
Rolls-Royce North American Technologies Inc. (USA)
Rolls-Royce Corporation (USA)
Inventor
Lighty, Kerry J.
Acker, Jonathan P.
Kremer, Douglas J.
Mazur, Steven
Whitlock, Mark E.
Abstract
A bleed valve assembly includes a manifold coupled to a case of a compressor of a gas turbine engine to control a flow of bleed air exiting the compressor, a valve housing coupled with the manifold, a piston configured to move selectively relative to the valve housing and the manifold, and one or more shims located between the valve housing and the piston.
An electrically actuated propeller pitch control system includes a propeller hub assembly, a propeller assembly, and a crosshead drive system. The propeller hub assembly rotates about the central axis during operation of watercraft. The propeller assembly is configured to selectively rotate a propeller blade. The crosshead drive system includes an electric motor, a transmission, and a lead screw that rotates about the central axis.
B63H 23/08 - Transmitting power from propulsion power plant to propulsive elements with mechanical gearing for transmitting drive from a single propulsion power unit with provision for reversing drive
75.
PROPELLER PITCH INDICATOR SYSTEMS FOR ELECTRICALLY CONTROLLABLE PITCH PROPELLER SYSTEMS ON WATERCRAFT
An electrically actuated propeller pitch control system includes a propeller hub, a propeller assembly, and a crosshead drive system. The propeller hub rotates about the central axis during operation of watercraft. The propeller assembly is coupled to rotate with the propeller hub during operation of the watercraft. The crosshead drive system includes an electric motor, a lead screw, and a pitch position indicator system configured to indicate a pitch angle of propeller blades.
Synchronisation methods for synchronising processor nodes of an Engine Control and Monitoring System (ECaMS) for an engine. A method comprises counting, at a first acquisition integrated circuit in a first processor node of the ECaMS, a first control cycle count, and storing at the first acquisition integrated circuit a first transmission slot index. The method further comprises counting a second control cycle count and storing a second transmission slot index at a second acquisition integrated circuit in a second processor node of the ECaMS. The method also comprises transmitting a message including the first control cycle count and transmission slot index from the first to second acquisition integrated circuits, and receiving the message at the second acquisition circuit. The method also comprises synchronising the first and second processor nodes using the first and second control cycle counts and transmission slot indexes.
A system for coupling at least one component to a blade of a gas turbine engine includes a blade holder and an intensifier tool. The intensifier tool includes a plate configured to contact the component and a heating device coupled to the plate. The system further includes an adhesive layer disposed between the component and the blade, a pressure strip coupled to the plate and the blade that fully encloses the plate, and a pressure applicator coupled to the plate. The adhesive layer has a uniform bond thickness along a length of the component due to pressure applied by the pressure applicator. Upon being heated by the heating device, the adhesive layer is cured, thereby coupling the component to the blade.
A DC power distribution and protection system comprising: a first DC power source (21), a first load (R1), a first power bus (31, 41) connecting the first power source (21) and the first load (R01), the first power bus (31, 41) comprising a high side voltage rail (31) and a low side voltage rail (41), a first solid state power controller (SSPC_A) arranged in the high side voltage rail (31) or low side voltage rail (41) at a DC power source side (61) of the voltage rail, and a second solid state power controller (SSPC_B) arranged in the same voltage rail (31, 41) as the first solid state power controller (SSPC_A) at a load side (62) of that voltage rail (31, 41) A first bypass line (51) is provided that connects the first DC power source (21) with the first load (R1) under bypassing of the first and second solid state power controllers (SSPC_A, SSPC_B), wherein the first bypass line (51) comprises a third solid state power controller (SSPC_R), and wherein the third solid state power controller (SSPC_R) is configured to be switched on only if the first and second solid state power controllers (SSPC_A, SSPC_B) are switched off.
H02H 7/26 - Sectionalised protection of cable or line systems, e.g. for disconnecting a section on which a short-circuit, earth fault, or arc discharge has occurred
The disclosure relates to a stator assembly for an electric machine. Example embodiments disclosed include a rotor assembly for an electric machine, the rotor assembly comprising: a rotor core; a plurality of magnets arranged around the rotor core; and a cylindrical rotor sleeve surrounding the plurality of magnets, wherein the rotor sleeve comprises a laminated composite material having an array of ferromagnetic pins extending through a thickness of the rotor sleeve.
B29C 70/32 - Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or coreShaping by spray-up, i.e. spraying of fibres on a mould, former or core on a rotating mould, former or core
B29K 105/10 - Condition, form or state of moulded material containing reinforcements, fillers or inserts of continuous length, e.g. cords, rovings, mats, fabrics, strands or yarns oriented
H02K 15/03 - Processes or apparatus specially adapted for manufacturing, assembling, maintaining or repairing of dynamo-electric machines of stator or rotor bodies having permanent magnets
H02K 15/12 - Impregnating, moulding insulation, heating or drying of windings, stators, rotors or machines
Engine Control and Monitoring Systems (ECaMS) for engines are disclosed. An ECaMS comprises a first processor node and a second processor node. The first processor node comprises a first acquisition integrated circuit (IC), a first output IC, and a first processor. The second processor node comprises a second acquisition IC, a second output IC, and a second processor. The first acquisition IC is connected directly to the second acquisition IC.
Methods for modifying an Engine Control and Monitoring System (ECaMS) for an engine. A method comprises identifying a provisioning deficit in the ECaMS, wherein the ECaMS comprises a first processor node and a second processor node. The first processor node comprises a first acquisition integrated circuit (IC), a first output IC, and a first processor. The second processor node comprises a second acquisition IC, a second output IC, and a second processor. The first acquisition IC is connected directly to the second acquisition IC. The method comprises connecting an expansion unit to the ECaMS. The expansion unit comprises one or more expansion unit ICs, said one or more expansion unit ICs being connected to one or more ICs of the ECaMS.
F02D 41/26 - Electrical control of supply of combustible mixture or its constituents characterised by the use of digital means using computer, e.g. microprocessor
A DC power distribution and protection system comprising: a first DC power source (21) having a positive terminal (211) and a negative terminal (212), a first load (R1), a first power bus (31, 41) connecting the first power source (21) and the first load (R01), a first solid state power controller (SSPC_A) integrated into the first power bus (31, 41) at a power source side (61) of the first power bus, and a second solid state power controller (SSPC_B) integrated into the first power bus (31, 41) at a load side (62) of the first power bus A first bypass line (51) is provided that extends between an upstream switching device (SSPC_A1) of the first solid state power controller (SSPC_A) and a downstream switching device (SSPC_B2) of the second solid state power controller (SSPC_B), the first bypass line (51) bypassing a downstream switching device (SSPC_A2) of the first solid state power controller (SSPC_A) and an upstream switching device (SSPC_B1) of the second solid state power controller (SSPC_B). The first bypass line (51) comprises at least one bypass switching device (SSPC_R1, SSCP_R2, CT), and is configured to be switched on only if the downstream switching device (SSPC_A2) of the first solid state power controller (SSPC_A) and the upstream switching device (SSPC_B1) of the second solid state power controller (SSPC_B) are switched off.
H02J 1/08 - Three-wire systemsSystems having more than three wires
H02J 13/00 - Circuit arrangements for providing remote indication of network conditions, e.g. an instantaneous record of the open or closed condition of each circuitbreaker in the networkCircuit arrangements for providing remote control of switching means in a power distribution network, e.g. switching in and out of current consumers by using a pulse code signal carried by the network
H02H 7/26 - Sectionalised protection of cable or line systems, e.g. for disconnecting a section on which a short-circuit, earth fault, or arc discharge has occurred
H02H 3/087 - Emergency protective circuit arrangements for automatic disconnection directly responsive to an undesired change from normal electric working condition, with or without subsequent reconnection responsive to excess current for DC applications
A power distribution system that comprises a first and second energy supply systems (11, 12), first and second electric drives (21, 22) associated with first and second input protections units (31, 32), and a power network connecting the first and second energy supply systems (11, 12) with the first and second electric drives (21, 22) The power network comprises a first and second power bus (41, 42) connecting the first and second energy supply systems (11, 21) with the first and second electric drives (21, 22), a first switching unit (51) associated with the first electric drive (21), and a second switching unit (52) associated with the second electric drive (22). The first switching unit (51) comprises a first input (511) from the first power bus (41), a first output (512) to the first power bus (41) or the first electric drive (21), and a second output (513) to the second switching unit (52). The second switching unit (52) comprises a first input (521) from the second power bus (42), a first output (522) to the second power bus (42) or the second electric drive (22), and a second input (524) from the first switching unit (51). The first switching unit (51) is configured to couple its first input (511) with its first output (512) when the input protection unit (31) of first electric drive (21) is switched off and configured to couple its input (511) with its second output (513) when the input protection unit (31) of the first electric drive (21) is switched on. The second switching unit (52) is configured to couple its second input (524) with its first output (522) to receive through its second input (524) power from the first power bus (41) and to couple the received power into the second power bus (42) or the second electric drive (21).
H02J 1/08 - Three-wire systemsSystems having more than three wires
B60L 3/00 - Electric devices on electrically-propelled vehicles for safety purposesMonitoring operating variables, e.g. speed, deceleration or energy consumption
H02J 4/00 - Circuit arrangements for mains or distribution networks not specified as ac or dc
84.
Adjustable fan track liner with slotted array active fan tip treatment for distortion tolerance
Rolls-Royce North American Technologies Inc. (USA)
Rolls-Royce Corporation (USA)
Inventor
Molnar, Jr., Daniel E.
Heeter, Robert W.
Rivers, Jonathan M.
Abstract
A gas turbine engine includes a fan and a fan case assembly. The fan includes a fan rotor configured to rotate about an axis of the gas turbine engine and a plurality of fan blades coupled to the fan rotor for rotation therewith. The fan case assembly extends circumferentially around the plurality of fan blades radially outward of the plurality of the fan blades.
F04D 29/68 - Combating cavitation, whirls, noise, vibration, or the likeBalancing by influencing boundary layers
F01D 11/08 - Preventing or minimising internal leakage of working fluid, e.g. between stages for sealing space between rotor blade tips and stator
F01D 17/12 - Final actuators arranged in stator parts
F04D 29/52 - CasingsConnections for working fluid for axial pumps
F01D 11/22 - Actively adjusting tip-clearance by mechanically actuating the stator or rotor components, e.g. moving shroud sections relative to the rotor
85.
Turbine shroud assemblies with inter-segment strip seal
A turbine shroud assembly comprising a first shroud segment, a second shroud segment, and a plurality of seals. The first shroud segment includes a first carrier segment and a first blade track segment having a first shroud wall that is formed to include a first recess that extends circumferentially into the first shroud wall. The second shroud segment includes a second carrier segment and a second blade track having a second shroud wall that is formed to include a second recess that extends circumferentially into the second shroud wall. The plurality of seals extend circumferentially into the first shroud segment and the second shroud segment to block gases from escaping the gas path radially between the first shroud segment and the second shroud segment.
An example machine-gear system that connects to a prime mover in which the prime mover may operate at a first rotational speed and the machine may operate at a different rotational speed. The gear system, of the machine-gear system, may be configured to connect the prime mover and the machine such that the prime mover operates at the first rotational speed and the machine may operate at the different speed. The gear system may be located within the housing of the machine, which may result in a more compact machine-gear system, than for other arrangements. In some examples, the gear system may include two or more stages. In some examples, the multiple stage gear systems may be configured to engage or disengage from one, or more, stages, which may result in a machine-gear system that operates at two or more different rotational speeds as the operational modes change.
The present disclosure relates to an electric drive apparatus 201, 202 comprising an inverter system 220, an electric motor 230 and a controller 290. The electric motor 230 includes a rotor 234 and a plurality of phase windings 221, 222, 223, 224. The inverter system 220 is configured to provide a respective current waveform 321, 322, 323, 324 to each of the phase windings 221, 222, 223, 224 of the electric motor 230. Each current waveform 321, 322, 323, 324 is defined by a group of electrical characteristics including: a frequency composition, a phase shift relative to a reference waveform 349, and an amplitude. For one or more of the current waveforms 321, 322, 323, 324, the controller 290 is configured to control one or more of the group of electrical characteristics to cause a periodically varying torque to be applied to the rotor 234.
F04D 13/06 - Units comprising pumps and their driving means the pump being electrically driven
H02P 27/06 - Arrangements or methods for the control of AC motors characterised by the kind of supply voltage using variable-frequency supply voltage, e.g. inverter or converter supply voltage using DC to AC converters or inverters
A shaft for a gas turbine engine includes a composite tube including a plurality of grooves extending along a longitudinal axis of the shaft. The shaft has a load fuse mechanism that has at least one metallic coupling that has a plurality of splines extending along the longitudinal axis of the shaft. Each of the plurality of splines is received within and engages with a corresponding groove of the composite tube to form a preloaded interference fit between the load fuse mechanism and the composite tube. The at least one metallic coupling includes a first portion defining a first diameter and a second portion extending from the first portion along the longitudinal axis. The second portion defines a second diameter that is greater than the first diameter. The second portion has a smooth annular outer surface devoid of any splines.
An aircraft comprises a machine body which encloses a turbofan gas turbine engine. The turbofan gas turbine engine includes a heat exchanger module, fan assembly, compressor module, turbine module, and exhaust module. The heat exchanger module communicates with the fan assembly by an inlet duct. The heat exchanger module includes first heat transfer elements that transfer heat energy from a first fluid within the transfer elements to an airflow passing over a surface of the transfer elements before entry of the airflow into a fan assembly inlet. The first fluid contained within transfer elements has a temperature, and the airflow passing over the transfer element surface has a temperature. The turbofan gas turbine engine further includes at least one second heat transfer element, with the or each second heat transfer element transfers heat energy from the first fluid to a second fluid.
F02C 7/14 - Cooling of plants of fluids in the plant
F02C 7/18 - Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
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 3/075 - 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 controlling flow ratio between flows
F02K 3/115 - Heating the by-pass flow by means of indirect heat exchange
Rolls-Royce North American Technologies, Inc. (USA)
Inventor
Hodgson, Benedict N.
Heeter, Robert W.
Smith, Alan W.
Baninajar, Hossein
Abstract
A stator housing assembly includes a stator housing and a stator sleeve. The stator sleeve including a combination of composite layers with different high strength fibers. The stator housing includes a first end section and a second end section that define a stator cavity configured to contain a pressurized cooling fluid. The stator sleeve defines a longitudinal axis and includes a plurality of layers of composite materials that include more than one high strength fiber material. High strength fibers may include carbon and glass fibers. Portions of the stator sleeve may have different combinations of high strength fiber materials and fiber orientations to optimize sleeve properties.
H02K 1/18 - Means for mounting or fastening magnetic stationary parts on to, or to, the stator structures
F02C 7/00 - Features, component parts, details or accessories, not provided for in, or of interest apart from, groups Air intakes for jet-propulsion plants
H02K 1/04 - Details of the magnetic circuit characterised by the material used for insulating the magnetic circuit or parts thereof
H02K 1/20 - Stationary parts of the magnetic circuit with channels or ducts for flow of cooling medium
H02K 7/18 - Structural association of electric generators with mechanical driving motors, e.g.with turbines
H02K 15/12 - Impregnating, moulding insulation, heating or drying of windings, stators, rotors or machines
91.
ELECTRIC MACHINE HAVING AN ADDITIONAL COOLING SYSTEM
The invention relates to an electric machine (1, 1') comprising: a stator (10, 10'), a rotor (11, 11') which can be rotated relative to the stator (10, 10'), a machine controller (16) which is configured to set a power of the electric machine (1, 1') and in which a threshold value (T) is stored which determines an output which can be set as the maximum in a normal operation of the electric machine (1, 1'), a cooling system (12) for cooling the stator (10, 10') and/or the rotor (11, 11'), wherein the cooling system (12) is designed to continuously discharge at least a maximum normal-operation heat output which can be maximally delivered in normal operation of the electric machine (1, 1'), and an additional cooling system (13) with a reservoir (130) for receiving a consumable fluid (131) which can be delivered to the stator (10, 10') and/or the rotor (11, 11') in order to cool the stator (10, 10') and/or the rotor (11, 11').
H02K 9/06 - Arrangements for cooling or ventilating by ambient air flowing through the machine having means for generating a flow of cooling medium with fans or impellers driven by the machine shaft
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
H02K 9/193 - Arrangements for cooling or ventilating for machines with closed casing and closed-circuit cooling using a liquid cooling medium, e.g. oil with provision for replenishing the cooling mediumArrangements for cooling or ventilating for machines with closed casing and closed-circuit cooling using a liquid cooling medium, e.g. oil with means for preventing leakage of the cooling medium
H02K 16/00 - Machines with more than one rotor or stator
H02K 1/04 - Details of the magnetic circuit characterised by the material used for insulating the magnetic circuit or parts thereof
H02K 3/30 - Windings characterised by the insulating material
H02K 11/33 - Drive circuits, e.g. power electronics
H02K 9/20 - Arrangements for cooling or ventilating for machines with closed casing and closed-circuit cooling using a liquid cooling medium, e.g. oil wherein the cooling medium vaporises within the machine casing
There is provided an electrical system, comprising: a DC source configured to provide a DC electrical power; a bus electrically coupled to the DC source, the bus comprising a load, a DC-DC converter having an input side and an output side; a switching arrangement electrically coupled to the DC-DC converter, the DC source and the bus; and a control system. The input side of the DC-DC converter is configured to receive a fraction of the DC electrical power provided by the DC source. The fraction is less than unity. The control system is configured to operate the switching arrangement to selectively configure the electrical system, in at least one of a voltage increase mode and a voltage decrease mode.
H02M 3/335 - Conversion of DC power input into DC power output with intermediate conversion into AC by static converters using discharge tubes with control electrode or semiconductor devices with control electrode to produce the intermediate AC using devices of a triode or a transistor type requiring continuous application of a control signal using semiconductor devices only
B64D 41/00 - Power installations for auxiliary purposes
93.
APPARATUS AND METHODS FOR CALCULATING AN ANGULAR SPEED OF A ROTARY COMPONENT
An apparatus for calculating an angular speed of a rotary component includes a processor circuitry configured to: receive an in-phase signal and a quadrature signal from a sensor arrangement, each signal relating to a position of the rotary component; arithmetically sum the in-phase signal and the quadrature signal generated by the sensor arrangement to produce a combined time-domain signal; and calculate an angular speed of the rotary component based on the combined time-domain signal. Methods of calculating an angular speed of a rotary component are also provided.
G01P 3/00 - Measuring linear or angular speedMeasuring differences of linear or angular speeds
G05B 19/4155 - 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 programme execution, i.e. part programme or machine function execution, e.g. selection of a programme
An annulus filler of a gas turbine engine includes an outer lid including a leading edge, a trailing edge, a first longitudinal edge, a second longitudinal edge, and an outer radial surface. The outer radial surface includes a first nominal surface portion and a second nominal surface portion. The outer radial surface further includes a protruding surface portion extending radially outwardly from each of the first nominal surface portion and the second nominal surface portion and a recessed surface portion extending radially inwardly from each of the first nominal surface portion and the second nominal surface portion. Each of the protruding surface portion and the recessed surface portion is configured to redirect an air drawn through the gas turbine engine.
The disclosure relates to a ducted fan aircraft propulsion system and to an aircraft incorporating such a propulsion system. Example embodiments include a ducted fan aircraft propulsion system (300), comprising: a duct (301); a central body portion (302) having first and second ends (303, 304) and extending through the duct (301); a payload portion (305) extending from the first end (303) of the central body portion (302); and a rotor (306) extending across an internal volume (307) of the duct (301) from the central body portion (302), wherein the duct (301) comprises an outwardly flared inlet end (308) such that an inlet air flow passage (309) between the central body portion (302) and an inner surface (310) of the duct (301) has a sectional area that decreases from the inlet end (308) of the duct (301) to the rotor (306).
A ducting arrangement for a gas turbine engine and a method of assembling such a ducting arrangement, wherein in the gas turbine engine includes an outer annular duct structure with an outer mount and an inner annular duct structure with an inner mount. The inner annular duct structure is configured to be received within the outer annular duct structure such that the inner mount and the outer mount are angularly aligned. In one aspect, the inner mount and the outer mount are coupled together by a tension tie to attach the outer annular duct structure to the inner annular duct structure, the tension tie being a cable or a wire. In another aspect, the inner mount and the outer mount are configured to be coupled together by a tension tie formed by a cable or a wire to attach the outer annular duct structure to the inner annular duct structure.
A power electronics cooling assembly with a housing for power electronics. The housing is mountable to a bulkhead for separating a fire zone from a non-fire zone of a gas turbine engine. In the non-fire zone, one or more ducts extend from the bulkhead to the housing. A fluid supply and return pipes extend through the one or more ducts from the bulkhead to the housing. The fluid supply and return pipes are for carrying an ignitable fluid coolant. A heat exchange structure arranged within the housing is configured to receive the ignitable fluid coolant from the fluid supply pipe, facilitate transfer of heat from the power electronics within the housing to the ignitable fluid coolant, and output the ignitable fluid coolant to the fluid return pipe. A system, gas turbine engine assembly and an aircraft comprising the power electronics cooling assembly are also provided.
A method of manufacturing a component including a metal alloy comprises measuring crystallographic texture of a volume of a component, determining a risk factor of the component for cold dwell fatigue failure, and adjusting metallurgical processing of the component based on the risk factor. Such risk analysis and mitigation may aid in improving the usage and operation of components including materials that are susceptible to cold dwell fatigue failure.
A power reduction system for an energy storage system of an aircraft includes a controller configured to control power reduction of power supplied from the energy storage system to an aircraft engine supply bus; and an override switch configurable in an override state and a non-override state. The override switch is configured to: in the non-override state, permit the controller to control the power reduction according to a default configuration comprising one or more parameters that trigger the power reduction; and in the override state, control the power reduction to be performed according to a relaxed configuration that at least one of relaxes and omits the one or more parameters in the default configuration.
B64D 31/00 - Power plant control systemsArrangement of power plant control systems in aircraft
B60L 58/10 - Methods or circuit arrangements for monitoring or controlling batteries or fuel cells, specially adapted for electric vehicles for monitoring or controlling batteries
B64D 27/24 - Aircraft characterised by the type or position of power plants using steam or spring force
100.
METHOD FOR MANUFACTURING A COMPOSITE BLADED DISK OR ROTOR
A method includes forming a moulded component that is axisymmetric about a component axis; segmenting the moulded component into a plurality of segments, each pair of adjacent segments including a pair of surfaces that is formed during segmentation of the moulded component; providing, via computerised numerical control machining, complementary finger joint profiles on the pair of surfaces of the each pair of adjacent segments; providing a plurality of slots on at least one of the pair of surfaces of the each pair of adjacent segments; positioning a plurality of blades partially within the plurality of slots; mating the complementary finger joint profiles provided on the pair of surfaces of the each pair of adjacent segments; and joining the each pair of adjacent segments to each other, such that the plurality of blades is retained within the plurality of slots.
