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公开(公告)号：US20240360786A1
公开(公告)日：2024-10-31
申请号：US18770780
申请日：2024-07-12
申请人： RTX CORPORATION
摘要： An aircraft propulsion system includes an energy conversion device that uses a cryogenic fuel and air to generate power and thermal energy, and a bottoming cycle where a working fluid is circulated within a closed circuit that includes a bottoming compressor section and a bottoming turbine section. A primary heat exchanger provides thermal communication of thermal energy from the energy conversion device to the working fluid of the bottoming cycle. A second heat exchanger is in thermal communication with the working fluid and a heat source other than from the energy conversion device for changing a temperature of the working fluid flow.
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公开(公告)号：US20240359814A1
公开(公告)日：2024-10-31
申请号：US18771038
申请日：2024-07-12
申请人： RTX CORPORATION
CPC分类号： B64D37/30 , B64D27/10 , F02C3/22 , F02C7/22 , F05D2230/60 , F05D2260/213
摘要： An aircraft propulsion system includes a core engine, a first bottoming cycle and a second bottoming cycle that utilize different working fluids having different critical temperatures such that each of the bottoming cycles have different heat absorption capabilities.
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公开(公告)号：US20240359813A1
公开(公告)日：2024-10-31
申请号：US18770884
申请日：2024-07-12
申请人： RTX CORPORATION
摘要： An aircraft propulsion system includes at least two gas turbine engines and a bottoming cycle system where a working fluid is circulated within a closed circuit that includes a bottoming compressor section and a bottoming turbine section. Each of the at least two gas turbine engines include a primary heat exchanger for communicating thermal energy into the working fluid of the bottoming cycle.
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公开(公告)号：US20240359812A1
公开(公告)日：2024-10-31
申请号：US18770830
申请日：2024-07-12
申请人： RTX CORPORATION
CPC分类号： B64D37/30 , B64D27/10 , F02C7/141 , F02C7/22 , F05D2260/213
摘要： An aircraft propulsion system includes a primary energy conversion device that uses a cryogenic fuel and air to generate power and thermal energy. The primary energy conversion device is mounted to a first structure of an aircraft. A bottoming cycle includes a working fluid that is circulated within a closed circuit that includes a bottoming compressor section and a bottoming turbine section. At least a portion of the bottoming cycle is mounted to a second structure of the aircraft that is different from the first structure. A primary heat exchanger provides communication of thermal energy from the primary conversion device to the working fluid of the bottoming cycle and is mounted within the first structure of the aircraft proximate the primary energy conversion device.
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公开(公告)号：US12128589B2
公开(公告)日：2024-10-29
申请号：US17858287
申请日：2022-07-06
申请人： RTX CORPORATION
发明人： Ken F. Blaney , Thomas E. Clark
CPC分类号： B29C43/361 , F01D9/04 , F01D9/06 , F01D11/08 , B29C2043/3626 , B29C2043/3665 , B29L2031/7504 , F05D2240/11 , F05D2300/6033 , F05D2300/614
摘要： A mandrel for a molding process includes a first portion and a second portion that form a mandrel having a channel between the first and second portions. At least one locking pin is configured to urge the first and second portions away from each other to establish a gap in response to inserting the locking pin into the channel along a respective end of the mandrel. A molding apparatus and method of forming a matrix composite component are also disclosed.
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公开(公告)号：US12123313B2
公开(公告)日：2024-10-22
申请号：US17366654
申请日：2021-07-02
申请人： RTX Corporation
发明人： Kevin Todd Lowe , Gwibo Byun , Albert P. Krejmas
CPC分类号： F01D21/003 , B64D27/18 , B64D43/00 , F02C9/00 , G01F1/661 , F05D2220/323 , F05D2260/80 , F05D2270/3061 , F05D2270/804
摘要： An aircraft includes a gas turbine engine and an optically-based measurement system. The gas turbine engine is configured to ingest a first mass flow and to exhaust a second mass flow. The optically-based measurement system is configured to determine the first and second mass flows in response to performing an imaging process on the gas turbine engine.
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公开(公告)号：US12123310B2
公开(公告)日：2024-10-22
申请号：US18480627
申请日：2023-10-04
申请人： RTX CORPORATION
发明人： Stephen G. Pixton , Gary Collopy , Ozhan Turgut
CPC分类号： F01D15/12 , F02C3/00 , F02C7/32 , F05D2220/323
摘要： A gas turbine engine according to an example of the present disclosure may include, among other things, a propulsor section including a propulsor having a plurality of propulsor blades, a geared architecture, a first spool including a first shaft that interconnects a first compressor and a first turbine, the first driving the propulsor through the geared architecture. The gas turbine engine is rated to provide an amount of thrust at ground idle, and the gas turbine engine is rated to provide an amount of thrust at maximum takeoff. A thrust ratio is defined as a ratio of the amount of thrust at ground idle divided by the amount of thrust at maximum takeoff. The thrust ratio can be less than or equal to 0.050.
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公开(公告)号：US12103699B2
公开(公告)日：2024-10-01
申请号：US17860751
申请日：2022-07-08
申请人： RTX Corporation
CPC分类号： B64D37/30 , B64D37/34 , B64D41/00 , F02C3/22 , F02C7/224 , F02C7/32 , F05D2220/323 , F05D2220/76 , F05D2260/40311
摘要： Aircraft propulsion systems have aircraft systems including at least one hydrogen tank and an aircraft-systems heat exchanger and engine systems includes at least a main engine core, a high pressure pump, a hydrogen-air heat exchanger, and a turbo expander. The main engine core includes a compressor section, a combustor section having a burner, and a turbine section arranged along an engine shaft. Hydrogen is supplied from the at least one hydrogen tank through a hydrogen flow path, passing through the aircraft-systems heat exchanger, the high pressure pump, the hydrogen-air heat exchanger, and the turbo expander, prior to being injected into the burner for combustion. The turbo expander is configured to impart power to the engine shaft.
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公开(公告)号：US12103078B2
公开(公告)日：2024-10-01
申请号：US17711235
申请日：2022-04-01
申请人： RTX Corporation
发明人： Guolin Oo
IPC分类号： B22F12/33 , B22F10/28 , B22F10/37 , B22F12/00 , B22F12/30 , B22F12/37 , B22F12/53 , B22F12/90 , B33Y10/00 , B33Y30/00
CPC分类号： B22F10/37 , B22F10/28 , B22F12/222 , B22F12/226 , B22F12/30 , B22F12/37 , B22F12/53 , B22F12/90 , B33Y10/00 , B33Y30/00
摘要： Disclosed herein is an additive manufacturing system that includes an energy source, a powder supply, and a build chamber. The build chamber includes a base plate and two or more variable build plates coupled to the base plate. The two or more variable build plates each have one or more adjustable features. The two or more variable build plates are configurable to position two or more parts at different heights relative to a top level of the build chamber. The additive manufacturing system also includes a control system configured to control the energy source to fuse material from the powder supply to at least one of the two or more parts while the two or more parts are respectively positioned by the two or more variable build plates at different heights relative to the top level of the build chamber.
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公开(公告)号：US12098678B2
公开(公告)日：2024-09-24
申请号：US16736970
申请日：2020-01-08
申请人： RTX Corporation
发明人： Timothy S. Snyder
CPC分类号： F02C7/228 , F02C7/232 , F02C9/263 , F05D2220/323 , F05D2270/303 , F23D2900/00015 , F23K2300/206 , F23N2235/24
摘要： A fuel delivery system for a combustor of a gas turbine engine including a primary fuel tank configured to store a primary fuel, a secondary fuel tank configured to store a secondary fuel, a swirler configured to produce a main flame within a combustion chamber of the combustor, and a fuel nozzle configured to produce a pilot flame within the combustion chamber of the combustor. The fuel nozzle includes a nozzle outlet that is located proximate to an end of the swirler or at the end of the swirler, the end of the swirler being located at an inlet of the combustor. The fuel delivery system also includes a primary fuel line fluidly connecting the primary fuel tank to the fuel nozzle and a secondary fuel line fluidly connecting the secondary fuel tank to the swirler.
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