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公开(公告)号：US20240359526A1
公开(公告)日：2024-10-31
申请号：US18307855
申请日：2023-04-27
发明人： Daniel ALECU
CPC分类号： B60H1/00321 , B64D33/08 , B60H2001/006 , G10K11/172
摘要： The heat exchanger can include one or more Helmholtz resonator having a cavity internal to the skin of the vehicle, the cavity delimited by a wall, the Helmholtz resonator having an aperture formed across the skin and fluidly connecting the cavity to the atmosphere, the cavity extending in the forward orientation of motion relative the aperture, an open cell structure filling at least a portion of the cavity; and a fluid passage internal to the skin, the fluid passage in thermal communication with the cavity via the wall of the cavity.
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公开(公告)号：US12129043B1
公开(公告)日：2024-10-29
申请号：US18238755
申请日：2023-08-28
CPC分类号： B64D33/08 , F01M5/005 , F16K1/22 , F16K31/041
摘要： A system is provided for an aircraft. This aircraft system includes a heat exchanger, a lubricant flow circuit and a bypass valve. The lubricant flow circuit includes an inlet passage, an outlet passage, a heat exchanger passage and a bypass passage. The heat exchanger passage extends through the heat exchanger. The bypass passage bypasses the heat exchanger. The heat exchanger passage and the bypass passage are fluidly coupled in parallel between the inlet passage and the outlet passage. The bypass valve is fluidly coupled inline along the lubricant flow circuit. The bypass valve is operable to regulate lubricant flow through the bypass passage. The bypass valve includes a rotary electric motor.
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公开(公告)号：US20240352890A1
公开(公告)日：2024-10-24
申请号：US18302963
申请日：2023-04-19
发明人： Dave MENHEERE
IPC分类号： F02C7/06 , F04B1/0465 , F04B1/1071 , F16N13/02
CPC分类号： F02C7/06 , F04B1/0465 , F04B1/1071 , F16N13/02 , F04B1/0408 , F04B1/0421 , F04B1/0439
摘要： The pump can have a support having a guide extending around an axis, a radial position of the guide relative the axis varying around the axis, and a first oil passage formed in the support; a rotary assembly mounted to the support via support bearings, and rotatable around the axis, the rotary assembly having a second oil passage and a cylinder, the cylinder extending radially relative the axis, an inlet port fluidly connecting the first oil passage to the cylinder, and an outlet port fluidly connecting the cylinder to the second oil passage, and a piston slidingly mounted in the cylinder, a radially-outer end of the piston further slidingly engaged with the guide.
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公开(公告)号：US12123305B2
公开(公告)日：2024-10-22
申请号：US17993517
申请日：2022-11-23
CPC分类号： F01D11/003 , F01D5/025 , F01D5/30 , F05D2220/32 , F05D2240/20 , F05D2240/55
摘要： A gas turbine engine rotor assembly is provided that includes a shaft, a rotor, and a seal assembly. The seal assembly is configured to seal between a first and second rotor compartments on opposite sides of the seal assembly. The seal assembly includes a seal groove and a split piston ring seal. The split piston ring seal is configured such that air in the first rotor compartment at P1 produces a radial force acting on the split piston ring seal, and air in the second rotor compartment at P2 produces a second force acting on the split piston ring seal, wherein the second force is directed radially inward and the first force is directed radially outward, and the second force is greater than the first force.
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公开(公告)号：US12116940B2
公开(公告)日：2024-10-15
申请号：US17215575
申请日：2021-03-29
CPC分类号： F02C9/20 , F02K3/04 , F04D27/0246 , F05D2270/023 , F05D2270/052 , F05D2270/053 , F05D2270/3011 , F05D2270/303 , F05D2270/304 , F05D2270/335 , F05D2270/71
摘要： Herein provided are methods and systems for controlling an engine having a variable geometry mechanism. A pressure ratio between a first pressure at an inlet of the engine and a predetermined reference pressure is determined. An output power for the engine is determined. The output power is adjusted based at least in part on the pressure ratio to obtain a corrected output power. A position control signal for a variable geometry mechanism of the engine is generated based on the corrected output power and the pressure ratio. The position control signal is output to a controller of the engine to control the variable geometry mechanism.
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公开(公告)号：US12116928B2
公开(公告)日：2024-10-15
申请号：US18185007
申请日：2023-03-16
发明人： David Menheere
CPC分类号： F02C3/085 , F02C6/20 , F02C3/045 , F02C3/08 , F02C3/09 , F02C3/10 , F02C3/103 , F02C3/107 , F02C3/13 , F02C7/36
摘要： An aircraft engine, has: a high-pressure spool having a high-pressure turbine drivingly engaged to a high-pressure compressor; and a low-pressure spool having: a first low-pressure turbine downstream of the high-pressure turbine; and a second low-pressure turbine downstream of the first low-pressure turbine, one or more of the first low-pressure turbine and the second low-pressure turbine drivingly engaged to a rotatable load, the first low-pressure turbine and the second low-pressure turbine radially offset from one another relative to a central axis of the aircraft engine.
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公开(公告)号：US20240337200A1
公开(公告)日：2024-10-10
申请号：US18130643
申请日：2023-04-04
发明人： Kashif MOHAMMED
CPC分类号： F01D25/12 , F02C7/14 , F03G7/0614 , F05D2260/20 , F05D2260/606 , F05D2300/505
摘要： An aircraft engine, has: a fluid system including a component adapted for containing a volume of the fluid, the fluid circuit further including a bypass conduit bypassing the component, and a valve fluidly connected to the fluid circuit upstream of the component relative to a flow of the fluid towards the component, the valve having an open configuration fluidly connecting the source of the fluid to the bypass conduit through the valve and a closed configuration in which the valve connects the source of the fluid to the component, the valve movable from the open configuration to the closed configuration in response to the fluid being at a first temperature, and the valve movable from the closed configuration to the open configuration in response to the fluid exerting an opening force on the valve and the fluid being at a second temperature different than the first temperature.
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公开(公告)号：US20240328361A1
公开(公告)日：2024-10-03
申请号：US18129637
申请日：2023-03-31
发明人： Sid-Ali Meslioui
IPC分类号： F02C7/24 , B32B3/12 , B32B3/26 , G10K11/168
CPC分类号： F02C7/24 , B32B3/12 , B32B3/266 , G10K11/168 , B32B2307/102 , B32B2605/18 , F05D2260/96
摘要： An acoustic panel is provided that includes a first skin, a second skin and a cellular core. The first skin includes a plurality of perforations. The perforations are configured to provide the first skin with a percentage of open area that changes according to a non-linear function as the first skin extends in a first direction. Spacing between at least some of the perforations vary as the first skin extends in the first direction. The cellular core is arranged between and is connected to the first skin and the second skin. The cellular core includes a plurality of chambers. Each of the chambers extends between the first skin and the second skin. Each of the chambers is fluidly coupled with a respective one or more of the perforations.
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公开(公告)号：US20240328349A1
公开(公告)日：2024-10-03
申请号：US18127155
申请日：2023-03-28
发明人： Dave MENHEERE
CPC分类号： F02C5/08 , F23R7/00 , F05D2240/35
摘要： A combustor assembly for a turbine engine includes a combustor assembly where a first combustion space is defined between a first closed end of a combustion chamber and a first piston, a second combustion space is defined between a second closed end of the combustion chamber and a second piston and a center combustion space is defined between the first piston and the second piston. An air inlet assembly provides for communication of inlet air to the first combustion space, the second combustion space and the center combustion space. First, second and center injectors are provided to inject fuel into a corresponding one of the first combustion space, the second combustion space, and the center combustion space. An exhaust outlet communicates an exhaust gas flow generated in each of the first combustion space, the second combustion space and the center combustion space to a turbine section.
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公开(公告)号：US20240327018A1
公开(公告)日：2024-10-03
申请号：US18129584
申请日：2023-03-31
发明人： Eric S. Durocher
摘要： A heat exchanger assembly for an aircraft includes a housing, a heat exchanger, and a nozzle. The housing includes an inner flow path wall, an outer flow path wall, an inner inflatable diaphragm, and an outer inflatable diaphragm. The inner flow path wall and the outer flow path wall form an air inlet and an air outlet. The inner inflatable diaphragm and the outer inflatable diaphragm form a venturi channel between the air inlet and the air outlet. The heat exchanger is disposed downstream of the venturi channel within the air flow path. The nozzle includes a nozzle housing disposed within the air flow path. The nozzle housing forms a nozzle inlet and a nozzle outlet. The nozzle outlet is disposed at the venturi channel.
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