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公开(公告)号：US12076827B1
公开(公告)日：2024-09-03
申请号：US18327939
申请日：2023-06-02
发明人： Dave Brosseau , Paul Dumitrache
IPC分类号： B23P19/04 , B23P11/02 , B23P19/02 , B23P19/027 , B25B27/02
CPC分类号： B23P19/04 , B23P11/02 , B23P19/022 , B23P19/025 , B23P19/027 , B25B27/026
摘要： A tool assembly for disassembling a crankshaft assembly with a main shaft received within a hollow extension shaft along a shaft axis and coupled thereto via an interference fit, the extension shaft having a fastener slot. The tool assembly includes a main tool body having a central bore, a main tool body inner surface circumscribing the central bore, and a main tool body outer surface having a fastener bore, the central bore dimensioned for axially receiving the extension shaft, with the fastener bore axially aligned with the extension shaft fastener slot. A fastener is concurrently fastenable to the main tool body via the fastener bore and the hollow extension shaft via the fastener slot. An actuator assembly with a linearly-displacing actuating element is coupled to the main tool body and applies a force, via the actuating element, against an end of the main shaft in a direction along the axis.
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公开(公告)号：US12065972B2
公开(公告)日：2024-08-20
申请号：US18092637
申请日：2023-01-03
发明人： Daniel Alecu , David Menheere
IPC分类号： F02C7/28 , F01D9/06 , F01D25/12 , F01D25/18 , F02C6/08 , F02C7/18 , F02C9/18 , F02C3/04 , F02C7/06 , F02C9/16
CPC分类号： F02C7/28 , F01D9/065 , F01D25/125 , F01D25/183 , F02C6/08 , F02C7/18 , F02C9/18 , F02C3/04 , F02C7/06 , F02C9/16 , F05D2220/32 , F05D2240/35 , F05D2240/55 , F05D2240/60 , F05D2260/221
摘要： Systems and methods for delivering a buffer fluid to a shaft seal of a gas turbine engine are provided. An exemplary system includes, a buffer fluid source, one or more first conduits providing fluid communication between the buffer fluid source and the shaft seal along a first route, and one or more second conduits providing fluid communication between the buffer fluid source and the shaft seal along a second route different from the first route. A heat exchanger is also disposed along the first route to facilitate heat transfer between buffer fluid in the one or more first conduits and a cooling fluid.
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公开(公告)号：US20240264029A1
公开(公告)日：2024-08-08
申请号：US18105649
申请日：2023-02-03
发明人： Jeremy Gonzalez , Jong Park
IPC分类号： G01M3/24
CPC分类号： G01M3/24
摘要： A method of and system for inspecting a sealed compartment within a gas turbine engine is provided. The method includes using at least one acoustic transmitter to produce at least one emitted acoustic signal into a compartment interior cavity. The acoustic transmitter is in communication with the at least one port. The array of acoustic sensors is used to sense acoustic signals. The acoustic sensors are disposed in proximity to the seal outside of the interior cavity of the sealed compartment. Each acoustic sensor is configured to sense emitted acoustic signals produced by the acoustic transmitter and to produce signal data representative of sensed acoustic signals. The presence or absence of a compromised region of the seal is determined using the signal data from at least one of the acoustic sensors of the array of acoustic sensors.
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公开(公告)号：US20240263786A1
公开(公告)日：2024-08-08
申请号：US18104899
申请日：2023-02-02
发明人： Kian McCaldon
摘要： A fuel mixture distribution system for a turbine engine assembly includes a combustor that includes a combustion chamber, a fuel mixture distributor that includes an air conduit defining a mixing chamber between an air inlet and an exit opening to the combustion chamber, and a plurality of fuel passages that are disposed in the air conduit where a fuel flow is introduced and mixed with air in the mixing chamber prior to flowing through the exit opening into the combustion chamber. The air conduit shape is defined to achieve the desired mixing and prevent flashback at all operating conditions.
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公开(公告)号：US20240263785A1
公开(公告)日：2024-08-08
申请号：US18104885
申请日：2023-02-02
发明人： Kian McCaldon
CPC分类号： F23R3/286 , F02C7/22 , F05D2220/32 , F05D2240/36
摘要： A fuel mixture distribution system for a turbine engine assembly includes a combustor that includes a wall defining a combustion chamber, a fuel mixture distributor that includes a mixing chamber that extends along an axis between a closed end and an exit opening to the combustion chamber, the mixing chamber shape being defined to achieve the desired mixing and prevent flashback at all operating conditions, and a plurality of fuel passages and a plurality of air passages that are disposed about a periphery of the mixing chamber within a common plane transverse to the axis. Each of the plurality of fuel passages and each of the plurality of air passages are angled to induce mixing of fuel and air within the mixing chamber prior to flowing through the exit opening into the combustion chamber.
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公开(公告)号：US20240263783A1
公开(公告)日：2024-08-08
申请号：US18426506
申请日：2024-01-30
发明人： Tin Cheung John Hu
摘要： A gas turbine engine includes an annular combustion chamber and an injector ring that is configured to introduce a hydrogen and gas mixture into the combustion chamber. The injector ring may include a hydrogen manifold cavity, hydrogen feed conduits that extend off of the hydrogen manifold cavity and open into a mixing region at an axial end of the injector ring, and gas feed conduits that also open into the mixing region to supply gas that mixes with the hydrogen. The hydrogen feed conduits may be tangentially-sloped, and the gas feed conduits may be radially and tangentially sloped.
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公开(公告)号：US12044135B1
公开(公告)日：2024-07-23
申请号：US18502161
申请日：2023-11-06
CPC分类号： F01D25/04 , F01D9/04 , F05D2220/323 , F05D2240/12 , F05D2260/96
摘要： A stator assembly for an aircraft engine, has: vanes distributed about a central axis, a vane having: an airfoil extending from a first end to a second end along a span and from a leading edge to a trailing edge along a chord, the airfoil having a pressure side and a suction side opposed to the pressure side; a slot within the airfoil, the slot extending in a direction having a component along the chord, the slot located between the pressure side and the suction side; a port at the leading edge, the port fluidly communicating with the slot and with the gaspath; a mass located within the slot, the mass movable within the slot to shift a center of gravity of the vane in a chordwise direction; and a biasing member biasing the mass in a direction opposite a pressure force generated by the flow of fluid.
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28.发明授权公开(公告)号：US12039713B2
公开(公告)日：2024-07-16
申请号：US18315629
申请日：2023-05-11
发明人： Justin Byers
CPC分类号： G06T7/0004 , B64F5/60 , G06T3/20 , G06T7/30 , G06T2207/10116 , G06T2207/30116 , G06T2207/30136
摘要： There is described a method for forming an inspection image of an object from radiographic imaging. The method has: forming the inspection image including scaling a feature of the object in one or more digital images to a common scale, the digital images including first and second digital images of the object, the first digital image having the feature at a first scale, the first digital image having a first grain diffraction pattern at the first scale, the second digital image having the feature at a second scale different from the first scale, the second digital image having a second grain diffraction pattern at the second scale, the second grain diffraction pattern different from the first grain diffraction pattern, the common scale common to both the first and second digital images after said scaling, and removing grain differences between the first and second grain diffraction patterns at the common scale.
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公开(公告)号：US20240229738A1
公开(公告)日：2024-07-11
申请号：US18151715
申请日：2023-01-09
IPC分类号： F02K1/48
CPC分类号： F02K1/48 , F05D2220/323 , F05D2300/506
摘要： An aircraft engine including a core casing extending circumferentially about an axis and defining a core flow passage, a nacelle located radially outward from and around the casing, and a bypass passage defined between the nacelle and the casing. A mixer includes a peripheral wall having a leading edge and a trailing edge, the leading edge attached to the casing. A first mixer portion and a second mixer portion are circumferentially spaced apart and respectively extend away from the leading edge from a first location to a second location. The first and second mixer portions respectively have a first and second stiffness, the first stiffness greater than the second stiffness and greater than a stiffness of an upstream portion of the wall extending from the first mixer portion at the first location toward the leading edge.
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30.发明公开公开(公告)号：US20240229703A9
公开(公告)日：2024-07-11
申请号：US17971239
申请日：2022-10-21
发明人： Richard Freer
CPC分类号： F01P7/16 , F01P11/08 , F01P2007/146
摘要： An aircraft propulsion system and method of cooling the same are provided. The system includes a hydraulic pump, an intermittent IC engine, a hydraulic motor, an engine oil pump, and a cooling system. The intermittent IC engine drives the hydraulic pump. The hydraulic motor is powered by the hydraulic pump and drives a propulsor fan. The cooling system includes a first heat exchanger (AIR-EO HEX) and a second heat exchanger (EO-HF HEX). The AIR-EO HEX transfers heat between flows of engine oil and ambient air. The EO-HF HEX transfers heat between flows of engine oil and hydraulic fluid. The hydraulic pump provides motive force to cause the hydraulic oil to pass through the EO-HF HEX and back to the at least one hydraulic pump. The engine oil pump provides motive force to pass the engine oil to and through the AIR-EO HEX, the EO-HF HEX, and the intermittent IC engine.
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