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公开(公告)号：US20240360787A1
公开(公告)日：2024-10-31
申请号：US18770979
申请日：2024-07-12
申请人： RTX CORPORATION
CPC分类号： F02C3/30 , F02C1/10 , F02C3/22 , F02C6/18 , F02C7/141 , F05D2220/323 , F05D2260/213
摘要： An aircraft propulsion system includes a core engine and a bottoming cycle where a working fluid is circulated within a closed circuit. A first heat exchanger is used to transfer heat from a portion of thermal energy from the exhaust gas flow to working fluid of the bottoming cycle. A fuel/working fluid heat exchanger provides the cryogenic fuel to cool the working fluid exhausted from a bottoming turbine and before a bottoming compressor.
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公开(公告)号：US20240318593A1
公开(公告)日：2024-09-26
申请号：US18529081
申请日：2023-12-05
申请人： RTX CORPORATION
CPC分类号： F02C6/18 , F03G7/0641 , F05D2220/323
摘要： An aircraft propulsion system includes a core engine assembly that generates an exhaust gas flow, a bottoming cycle that includes a bottoming fluid flow that is expanded through a bottoming turbine, a first heat exchanger where heat from the exhaust gas flow is transferred to heat the bottoming fluid flow, and a second heat exchanger where heat from a secondary heat source is transferred to heat the bottoming fluid flow. The second heat exchanger is disposed upstream of the first heat exchanger such that heat from the secondary heat source preheats the bottoming fluid flow prior to accepting heat from the exhaust gas flow in the first heat exchanger.
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公开(公告)号：US20240254917A1
公开(公告)日：2024-08-01
申请号：US18591389
申请日：2024-02-29
申请人： RTX Corporation
CPC分类号： F02C6/006 , F02C7/08 , F02C7/36 , F05D2260/10 , F05D2260/213 , F05D2260/232
摘要： An engine system includes a turbine engine including a compressor section, a combustor section having a burner, a turbine section, and a nozzle in an open-loop configuration. The engine system also includes a bottom-cycle apparatus and an exhaust heat exchanger downstream of the turbine section of the turbine engine configured to reject heat from the turbine engine to the bottoming-cycle apparatus and create a cooled turbine exhaust in the turbine engine. The engine system further includes an exhaust compressor arranged downstream of the exhaust heat exchanger and upstream of the nozzle of the turbine engine configured to compress the cooled turbine exhaust stream and increase a pressure of the cooled turbine exhaust stream prior to exiting the nozzle of the turbine engine.
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公开(公告)号：US20240010350A1
公开(公告)日：2024-01-11
申请号：US17860733
申请日：2022-07-08
申请人： RTX Corporation
CPC分类号： B64D37/30 , F02D41/0027 , B64D37/34 , B64D2041/005
摘要： Aircraft engine systems include a core assembly having at least a burner section and a fuel cell configured to generate electrical power. A cryogenic fuel source is configured to supply a fuel through a fuel supply line to each of the burner section and the fuel cell for reaction to generate the electrical power. A system controller is configured to direct fuel to each of the combustor section and the fuel cell. The controller determines if an amount of fuel in the fuel supply line is in excess of that necessary for operation of the core assembly and, based on a determination that excess fuel is present, the controller is configured to direct at least a portion of the excess fuel from the fuel supply line to the fuel cell to generate the electrical power.
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公开(公告)号：US20230392524A1
公开(公告)日：2023-12-07
申请号：US18233695
申请日：2023-08-14
申请人： RTX Corporation
CPC分类号： F01K25/005 , F01K7/12 , F01K7/16 , F01K15/02 , F01K27/02
摘要： A powerplant is provided that includes an engine and a water recovery system. The engine includes an engine combustor, an engine turbine, a flowpath and a fluid delivery system. The flowpath extends out of the engine combustor and through the engine turbine. The fluid delivery system includes a hydrogen reservoir and an oxygen reservoir. The hydrogen reservoir is configured to store fluid hydrogen as liquid hydrogen. The oxygen reservoir is configured to store fluid oxygen as liquid oxygen. The fluid delivery system is configured to provide the fluid hydrogen and the fluid oxygen for combustion within the engine combustor to produce combustion products within the flowpath. The water recovery system is configured to extract water from the combustion products. The water recovery system is configured to provide the water to a component of the powerplant.
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公开(公告)号：US20240360791A1
公开(公告)日：2024-10-31
申请号：US18770803
申请日：2024-07-12
申请人： RTX CORPORATION
CPC分类号： F02C7/141 , F02C1/10 , F02C3/22 , F02C6/18 , F02C7/32 , F05D2220/323 , F05D2260/213
摘要： An aircraft propulsion system includes 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 first heat exchanger provides for thermal energy from a first heat source to be input into the working fluid of the bottoming cycle. A second heat exchanger that is downstream from the first heat exchanger communicates additional thermal energy from a second heat source into the working fluid of the bottoming cycle after the thermal energy from the first heat source is input into the working fluid.
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公开(公告)号：US12071257B2
公开(公告)日：2024-08-27
申请号：US17860733
申请日：2022-07-08
申请人： RTX Corporation
CPC分类号： B64D37/30 , B64D37/34 , F02D41/0027 , B64D2041/005
摘要： Aircraft engine systems include a core assembly having at least a burner section and a fuel cell configured to generate electrical power. A cryogenic fuel source is configured to supply a fuel through a fuel supply line to each of the burner section and the fuel cell for reaction to generate the electrical power. A system controller is configured to direct fuel to each of the combustor section and the fuel cell. The controller determines if an amount of fuel in the fuel supply line is in excess of that necessary for operation of the core assembly and, based on a determination that excess fuel is present, the controller is configured to direct at least a portion of the excess fuel from the fuel supply line to the fuel cell to generate the electrical power.
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公开(公告)号：US20240262523A1
公开(公告)日：2024-08-08
申请号：US18405712
申请日：2024-01-05
申请人： RTX CORPORATION
CPC分类号： B64D33/02 , B64D33/04 , B64D2033/0286
摘要： A propulsion system for an aircraft includes a gas generating core engine, a propulsor that is driven by an exhaust gas flow that is generated by the core engine, and an inlet assembly where an inlet airflow is communicated to the core engine. The inlet assembly is disposed aft of the core engine and includes a turning duct that directs inlet air into the core engine, and a particle exhaust outlet that directs particulates away from the core engine.
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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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