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公开(公告)号：US12078084B1
公开(公告)日：2024-09-03
申请号：US18108336
申请日：2023-02-10
Applicant: Raytheon Technologies Corporation
Inventor： Neil J. Terwilliger , Joseph B. Staubach
CPC classification number: F01K11/02 , F01K7/223 , F01K15/02 , F05D2220/72
Abstract: A turbine engine assembly includes a core engine that generates an exhaust gas flow, a condenser where water is extracted from the exhaust gas flow, an evaporator where heat is input into the water that is extracted by the condenser into a first steam flow, a steam turbine where the first steam flow is expanded and cooled, and a superheater where additional heat is input into the first steam flow that is exhausted from the steam turbine to generate a second steam flow. The second steam flow is injected into a core flow path of the core engine.
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公开(公告)号：US20240253806A1
公开(公告)日：2024-08-01
申请号：US18102164
申请日：2023-01-27
Applicant: Raytheon Technologies Corporation
Inventor： Neil J. Terwilliger , Marc J. Muldoon
IPC: B64D37/30
CPC classification number: B64D37/30 , B64D2041/005 , B64D2221/00
Abstract: A cryogenic fueled aircraft propulsion system includes a core engine where fuel is mixed with compressed air and ignited to generate a high energy exhaust gas flow, a fuel system that is configured to supply the fuel to the core engine, a cryogenic fuel tank for storing fuel cryogenically in a liquid phase, a gas collection system where boil off gas from the fuel system is collected, a fuel cell system where a flow of collected boil off gas is utilized to generate electric power, and an electrical coupling where electric power generated by the fuel cell is communicated to location outside of the aircraft.
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公开(公告)号：US20240141837A1
公开(公告)日：2024-05-02
申请号：US18311460
申请日：2023-05-03
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： Jesse M Chandler , Marc J. Muldoon , Jon E. Sobanski , Neil J. Terwilliger , Joseph B. Staubach
CPC classification number: F02C7/22 , F02C7/18 , F05D2260/211
Abstract: A propulsion system for an aircraft includes a gas generating core engine generates an exhaust gas flow that is expanded through a turbine section, a power turbine driven by the exhaust gas flow, a propulsor coupled to the power turbine, a hydrogen fuel system configured to supply hydrogen fuel to the combustor through a fuel flow path, a condenser arranged along the core flow path and configured to extract water from the exhaust gas flow, and an evaporator arranged along the core flow path receiving a portion of the water extracted by the condenser to generate a steam flow that is injected into the core flow path upstream of the turbine section.
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公开(公告)号：US20240082750A1
公开(公告)日：2024-03-14
申请号：US17943817
申请日：2022-09-13
Applicant: Raytheon Technologies Corporation
Inventor： Andressa L. Johnson , Neil J. Terwilliger
CPC classification number: B01D5/0006 , B01D5/0081 , B01D5/009 , B64D33/04 , B01D2259/4575
Abstract: A powerplant is provided that includes a flowpath, a combustor and a water extraction system. The combustor is configured to generate combustion products and direct the combustion products through the flowpath. The combustion products are configured from or otherwise include water vapor. The water extraction system is arranged with the flowpath downstream of the combustor. The water extraction system includes a condensation seeder and a collector. The condensation seeder is configured to direct a plurality of small water droplets into the flowpath to promote condensation of the water vapor to grow the small water droplets into a plurality of large water droplets. The collector is configured to collect the large water droplets.
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公开(公告)号：US20240026824A1
公开(公告)日：2024-01-25
申请号：US17871270
申请日：2022-07-22
Applicant: Raytheon Technologies Corporation
Inventor： Neil J. Terwilliger , Brandon M. Evans
CPC classification number: F02C7/224 , F02C7/32 , F02C7/141 , F05D2260/10 , F05D2260/232 , F05D2260/213
Abstract: A system includes a top cycle and a bottoming cycle. The top cycle is an engine having a combustor. The combustor receives a fuel. The combustor is capable of igniting a mix of fuel and a gas, and creating products of combustion. Products of the combustion pass downstream through a first heat exchanger. The bottoming cycle has a bottoming cycle working fluid receiving a first amount of heat through the first heat exchanger. The bottoming cycle produces work from the first amount of heat. The bottoming cycle working fluid then passes through a second heat exchanger and rejects a second lesser amount of heat. A source housing fuel is delivered to the combustor via the second heat exchanger. The bottoming cycle working fluid provides heat to the fuel being delivered to the combustor. The source is configured to maintain the fuel at a temperature equal to or below 0° F.
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Patent Agency Ranking
公开(公告)号：US11753993B1
公开(公告)日：2023-09-12
申请号：US17669632
申请日：2022-02-11
Applicant: Raytheon Technologies Corporation
Inventor： Neil J. Terwilliger , Joseph E. Turney , Joseph B. Staubach
CPC classification number: F02C7/14 , F02C3/22 , F02C3/30 , F02C6/006 , F02C7/141 , F02C7/18 , F02C7/224 , F05D2220/323 , F05D2240/35 , F05D2260/207 , F05D2260/213 , F05D2260/232
Abstract: Aircraft engines include a turbine engine comprising a compressor section, a burner section, and a turbine section arranged along a shaft, with a core flow path through the turbine engine such that exhaust from the burner section passes through the turbine section, a condensing assembly arranged downstream of the turbine section of the turbine engine along the core flow path, and an exhaust compressor arranged downstream of the condensing assembly along the core flow path. The condensing assembly is configured to reduce a mass flow of the exhaust compressor by condensing water vapor from the core flow and removing liquid water from the core flow.
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公开(公告)号：US20230258126A1
公开(公告)日：2023-08-17
申请号：US17670080
申请日：2022-02-11
Applicant: Raytheon Technologies Corporation
Inventor： Neil J. Terwilliger , Walter A. Ledwith, JR. , David L. Ma , Joseph B. Staubach
Abstract: A powerplant is provided for an aircraft. This powerplant includes an engine and an energy 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 is configured to provide fluid hydrogen and fluid oxygen for combustion within the engine combustor to produce combustion products within the flowpath. The energy recovery system includes an energy recovery system condenser, an energy recovery system pump, an energy recovery system evaporator and an energy recovery system turbine. The energy recovery system pump is configured to pump liquid water from the energy recovery system condenser to the energy recovery system evaporator. The energy recovery system evaporator is configured to transfer heat from the combustion products into the liquid water to evaporate at least some of the liquid water into water vapor to drive the energy recovery system turbine.
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公开(公告)号：US11725544B1
公开(公告)日：2023-08-15
申请号：US17670043
申请日：2022-02-11
Applicant: Raytheon Technologies Corporation
Inventor： Neil J. Terwilliger , Walter A. Ledwith, Jr. , Joseph B. Staubach , David L. Ma
CPC classification number: F01K25/005 , F01K7/12 , F01K7/16 , F01K15/02 , F01K27/02
Abstract: 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：US20230212985A1
公开(公告)日：2023-07-06
申请号：US18115986
申请日：2023-03-01
Applicant: Raytheon Technologies Corporation
Inventor： Daniel Bernard Kupratis , Neil J. Terwilliger , Michael M. Romero
CPC classification number: F02C7/32 , F02C7/36 , F05D2260/40311 , F16H3/724
Abstract: A disclosed drive assembly for an auxiliary power unit includes a first drive shaft driven by an auxiliary power unit, a second drive shaft driven by a first electric motor, a differential gear system including a ring gear driven by the second drive shaft, a and planet gears supported within a carrier attached to the ring gear. The first drive shaft and an output shaft are coupled to the planet gears and a generator is driven by the output shaft. The electric motor and the auxiliary power unit combine to drive the output shaft.
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公开(公告)号：US12180893B2
公开(公告)日：2024-12-31
申请号：US18329044
申请日：2023-06-05
Applicant: Raytheon Technologies Corporation
Inventor： Neil J. Terwilliger , Joseph B. Staubach
Abstract: A propulsion system for an aircraft includes a core engine that includes a core flow path where air is compressed in a compressor section, communicated to a combustor section, mixed with a gaseous fuel and ignited to generate an exhaust gas flow that is expanded through a turbine section. A fuel system supplies a fuel to the combustor through a fuel flow path, a first heat exchanger thermally communicates a first heat load into a cooling flow, a turboexpander where a heated cooling flow from the first heat exchanger is expanded to generate shaft power and cooled to provide a cooled cooling flow, and a second heat exchanger thermally communicates a second heat load to the cooled cooling flow that is communicated from the turboexpander, cooling flow from the second heat exchanger is communicated to the combustor section.
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