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公开(公告)号：US20240227050A9
公开(公告)日：2024-07-11
申请号：US17971108
申请日：2022-10-21
发明人： Daniel Alecu , Laslo T. Diosady
摘要： A system for forming a nozzle inlet of a nozzle includes a nozzle body and an electro-chemical machining (ECM) assembly. The nozzle body includes an external surface. The nozzle body forms a nozzle orifice and a manifold passage. The nozzle orifice extends through the nozzle body between and to a nozzle inlet and a nozzle outlet. The nozzle inlet is disposed at the manifold passage. The nozzle outlet is disposed at the external surface. The ECM assembly is installed on the nozzle body. The ECM assembly includes a machining tool and a flexible line. The machining tool is disposed at the nozzle inlet. The flexible line is attached to the machining tool. The flexible line extends through the nozzle outlet from the machining tool to an exterior of the nozzle body.
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公开(公告)号：US12031489B2
公开(公告)日：2024-07-09
申请号：US17382922
申请日：2021-07-22
CPC分类号： F02C9/22 , F04D27/001 , F05D2220/323 , F05D2260/81 , F05D2270/301 , F05D2270/304 , F05D2270/306 , F05D2270/71
摘要： A system and a method for configuring at least one variable geometry mechanism (VGM) of an aircraft engine are provided. Pass-off testing data for the aircraft engine is obtained, the pass-off testing data indicative of an actual value of at least one operating parameter of the aircraft engine. Based on the pass-off testing data, at least one trim value to be used to adjust a setting of the at least one VGM to bring the actual value of the at least one operating parameter towards a target value is determined, a running line of the aircraft engine being substantially constant when the actual value of the at least one operating parameter is at the target value. The setting of the at least one VGM is adjusted, during pass-off testing of the aircraft engine, using the at least one trim value.
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公开(公告)号：US12030651B2
公开(公告)日：2024-07-09
申请号：US17142085
申请日：2021-01-05
发明人： Xi Wang
CPC分类号： B64D27/02 , B64D27/24 , B64D33/08 , F16H1/28 , F16H57/02 , F16H57/0416 , B64D2027/026 , F16H2057/02034 , F16H2057/02043
摘要： A hybrid-electric powertrain system for aircraft includes a gearbox having a first rotary shaft for output to drive an air mover for aircraft thrust. The system includes a first prime mover connected by a second rotary shaft to the gearbox for power input to the gearbox. Further, the system includes a second prime mover connected by a third rotary shaft to the gearbox. The second prime mover can have a hollow core, and at least one of the first and second rotary shafts passes through the hollow core and the third rotary shaft.
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公开(公告)号：US20240218809A1
公开(公告)日：2024-07-04
申请号：US18091517
申请日：2022-12-30
发明人： Hien Duong , Vijay Kandasamy
CPC分类号： F01D25/162 , F01D9/02
摘要： A strut includes a strut body extending in a radial direction and defining an airfoil shape in cross-section perpendicular to the radial direction. The airfoil shape includes a leading edge and a trailing edge. An extraction inlet is defined through an exterior surface of the strut body, in fluid communication with an internal conduit of the strut body. An injection outlet is defined through the exterior surface of the strut body, in fluid communication with the internal conduit for fluid communication through the internal conduit from the extraction inlet to the injection outlet.
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公开(公告)号：US20240208657A1
公开(公告)日：2024-06-27
申请号：US18088249
申请日：2022-12-23
发明人： Michel Bousquet , Kevin Nguyen
摘要： An aircraft system is provided that includes a first propulsor rotor, a second propulsor rotor and an electric machine. The first propulsor rotor is rotatable about an axis. The second propulsor rotor is rotatable about the axis. The electric machine includes a first electric machine rotor, a second electric machine rotor and an electric machine stator radially between the first electric machine rotor and the second electric machine rotor. The first electric machine rotor is rotatable about the axis and rotatably connected to the first propulsor rotor. The first electric machine rotor and the electric machine stator form a first motor configured to drive rotation of the first propulsor rotor. The second electric machine rotor are rotatable about the axis and rotatably connected to the second propulsor rotor. The second electric machine rotor and the electric machine stator form a second motor configured to drive rotation of the second propulsor rotor.
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公开(公告)号：US20240208073A1
公开(公告)日：2024-06-27
申请号：US18397965
申请日：2023-12-27
发明人： Philippe Morin , Canam Hoang , Jean-Francois Collette , Pierre-Luc Nault , Guillaume Whittom , Guillaume Fortier
CPC分类号： B25J11/0065 , B25J9/1664 , B25J9/1692 , B25J9/1697 , B25J15/0019 , B25J19/0058
摘要： A polishing system includes a robotic polishing assembly, a calibration system, a belt cleaning assembly, and a controller. The robotic polishing assembly includes a robotic arm and an end effector. The end effector includes a polishing arm, a motor, and a tool head. The calibration system includes an imaging device. The belt cleaning assembly includes a first lateral brush and a second lateral brush. The controller is in signal communication with the robotic polishing assembly and the calibration system. The controller includes a processor in communication with a non-transitory memory storing instructions, which instructions when executed by the processor, cause the processor to identify a cleaning requirement for the tool head and control the robotic polishing assembly to clean the tool head by moving the tool head to engage the belt cleaning assembly.
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公开(公告)号：US12006882B1
公开(公告)日：2024-06-11
申请号：US18331687
申请日：2023-06-08
CPC分类号： F02C9/40 , F02B53/02 , F02B53/10 , F02B2053/005 , F05D2220/323
摘要： A rotary engine, has: an outer body defining a rotor cavity; a rotor within the rotor cavity and defining at least one chamber; a pilot subchamber defined by the outer body and having an outlet in communication with the rotor cavity; a main fuel source of a heavy fuel; an alternative fuel source of an alternative fuel; a main injector having a tip in communication with the rotor cavity at a location spaced apart from the outlet of the pilot subchamber, the main injector selectively fluidly connectable to the main fuel source or to the alternative fuel source; and a controller configured for: determining that the rotary engine is in a vicinity of a city or an airport; and operating the main injector in a first configuration in which the main injector fluidly connects the alternative fuel source to the rotor cavity while disconnecting the main fuel source.
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公开(公告)号：US12000758B2
公开(公告)日：2024-06-04
申请号：US17343705
申请日：2021-06-09
发明人： Antwan Shenouda
摘要： In accordance with at least one aspect of this disclosure, a fluid system of an aircraft includes a primary fluid conduit that conveys a primary fluid, and a leak detection system disposed around at least a portion of the primary fluid conduit and forming one or more detection volumes. The leak detection system determines whether there is a primary fluid leak into the one or more detection volumes by sensing a pressure change in the one or more detection volumes.
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公开(公告)号：US12000495B2
公开(公告)日：2024-06-04
申请号：US17380573
申请日：2021-07-20
发明人： Hugues Pellerin
CPC分类号： F16K17/065 , F16K1/126 , Y10T137/3367
摘要： A referenced pressure valve for a fluid system having a housing including: an inner wall enclosing a cavity providing fluid communication between the inlet and the outlet; a rim in the cavity defining a bypass passage circumscribed outwardly by the inner wall and inwardly by the rim, an upstream passage located between an upstream end of the cavity and the rim, and a downstream passage located between the rim and a downstream end of the cavity. A rib extends outwardly from the rim to the inner wall through the bypass passage, and a piston assembly, received within a chamber circumscribed outwardly by the rim, includes a piston movable relative to the rim between a position in which the piston obstructs the flow path at the upstream passage and a position in which the piston is at least partially clear of the path to permit flow along the path.
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公开(公告)号：US11999497B2
公开(公告)日：2024-06-04
申请号：US18353162
申请日：2023-07-17
发明人： Pierre Bertrand , Jean Thomassin
CPC分类号： B64D27/24 , B64D27/12 , B64D29/02 , B64D27/026
摘要： The aircraft includes a fuselage and at least one wing extending from the fuselage. The wing includes first and second original portions and a plug portion positioned between the first and second original portions. A propulsion system is positioned on the at least one wing. The propulsion system includes at least one electric powerplant and at least one combustion powerplant. Each powerplant delivers power to a respective air mover for propelling the aircraft. The electric powerplant and/or the combustion powerplant is positioned outboard from the plug portion.
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