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公开(公告)号：US20240384659A1
公开(公告)日：2024-11-21
申请号：US18199742
申请日：2023-05-19
Applicant: Raytheon Technologies Corporation
Inventor： Jon E. Sobanski , Neil J. Terwilliger
Abstract: A turbine engine is provided that includes a bypass flowpath, a plurality of upstream vanes and a plurality of downstream vanes. The bypass flowpath is fluidly coupled with and downstream of a fan section. The bypass flowpath bypasses a turbine engine core. The upstream vanes are arranged circumferentially about an axis in an upstream vane array. Each of the upstream vanes extends radially across the bypass flowpath. The downstream vanes are arranged circumferentially about the axis in a downstream vane array. The downstream vanes are circumferentially interspersed with the upstream vanes. Each of the downstream vanes extends radially across the bypass flowpath. A first of the downstream vanes is axially offset from a first of the upstream vanes along the axis.
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公开(公告)号：US12129787B2
公开(公告)日：2024-10-29
申请号：US18102356
申请日：2023-01-27
Applicant: Raytheon Technologies Corporation
Inventor： Joseph B. Staubach , Joseph E. Turney , Neil J. Terwilliger
IPC: F02C3/30
CPC classification number: F02C3/30 , F05D2220/323 , F05D2240/35
Abstract: A turbine engine assembly an inter-turbine burner that is disposed between at least two of a plurality of turbine stages where an additional amount of fuel is mixed with an exhaust gas flow to generate a reheated gas flow. A condenser extracts water from the reheated gas flow and an evaporator system generates a steam flow from at least a portion of water that is extracted by the condenser for injection into the core airflow.
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公开(公告)号：US12071890B1
公开(公告)日：2024-08-27
申请号：US18119182
申请日：2023-03-08
Applicant: Raytheon Technologies Corporation
Inventor： Neil J. Terwilliger
CPC classification number: F02C3/30 , F01D25/32 , F05D2220/323 , F05D2220/62 , F05D2220/72 , F05D2260/213
Abstract: A powerplant includes a turbine engine core configured to power a mechanical load. The turbine engine core includes a core compressor section, a core combustor section and a core turbine section. A recovery system includes a condenser and an evaporator. A core flowpath extends sequentially through the core compressor section, the core combustor section, the core turbine section, the evaporator and the condenser from an inlet into the core flowpath to an exhaust from the core flowpath. The recovery system is configured to condense water vapor flowing through the core flowpath into water using the condenser. The recovery system is configured to evaporate the water into steam using the evaporator and to provide the steam to the turbine engine core during a first mode of operation. The recovery system is configured to flow the water through the evaporator during a second mode of operation.
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公开(公告)号：US20240254927A1
公开(公告)日：2024-08-01
申请号：US18102295
申请日：2023-01-27
Applicant: Raytheon Technologies Corporation
Inventor： Neil J. Terwilliger , Marc J. Muldoon
CPC classification number: F02C9/40 , F02C7/22 , F05D2220/323 , F05D2240/35 , F05D2260/20
Abstract: A cryogenic fueled aircraft propulsion system includes a core engine that generates a high energy exhaust gas flow, a fuel system that is configured to supply a fuel to the core engine, a cryogenic fuel tank that is configured to maintain fuel in a liquid phase during aircraft operating conditions, a gas collection system where boil off gas from the cryogenic fuel tank is collected, and a fuel reliquification system where collected boil off gas from the cryogenic fuel tank is transformed into a liquid phase.
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公开(公告)号：US20240253821A1
公开(公告)日：2024-08-01
申请号：US18102154
申请日：2023-01-27
Applicant: Raytheon Technologies Corporation
Inventor： Neil J. Terwilliger , Marc J. Muldoon
Abstract: A cryogenic fueled aircraft propulsion maintenance system includes a fuel system of an aircraft, the fuel system includes a cryogenic fuel tank that is configured to maintain the fuel in a liquid phase during aircraft operating conditions, a gas collection system where boil off gas from the fuel system is collected, and a fuel reliquification system that is configured to receive boil off gas from the gas collection system and transform the boil off gas into a liquid phase as liquid fuel.
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Patent Agency Ranking
公开(公告)号：US20240026816A1
公开(公告)日：2024-01-25
申请号：US17871581
申请日：2022-07-22
Applicant: Raytheon Technologies Corporation
Inventor： Neil J. Terwilliger , Walter A. Ledwith, JR. , Joseph B. Staubach , David Lei Ma
Abstract: An energy supply system includes a source of gas which is at a pressure that is equal to or greater than an atmospheric pressure. The source of gas is configured to deliver the gas into a combustor where it is mixed with a fuel. The combustor is also connected to receive a source of steam. The combustor is operable to provide combustion. Products of the combustion downstream of the combustor are connected to be delivered across a turbine rotor. The turbine rotor is provided with a shaft. The turbine shaft drives a generator. An evaporator downstream of the turbine receives the products of the combustion. The evaporator is operable to heat a source of water. The source of water downstream of the evaporator is the source of steam delivered into the combustor. The gas includes greater than 80% oxygen and the fuel includes hydrogen.
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公开(公告)号：US20230258125A1
公开(公告)日：2023-08-17
申请号：US17670045
申请日：2022-02-11
Applicant: Raytheon Technologies Corporation
Inventor： Neil J. Terwilliger , Joseph B. Staubach
CPC classification number: F02C6/006 , F02C7/08 , F02C7/36 , F05D2260/10 , F05D2260/213 , F05D2260/232
Abstract: 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：US20230258106A1
公开(公告)日：2023-08-17
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 , F01K27/02 , F01K7/12 , F01K7/16 , F01K15/02
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：US11603798B1
公开(公告)日：2023-03-14
申请号：US17669680
申请日：2022-02-11
Applicant: Raytheon Technologies Corporation
Inventor： Neil J. Terwilliger , Joseph B. Staubach , Joseph E. Turney
Abstract: Aircraft engines include a burner section and a turbine section arranged along a shaft, wherein an exhaust from the burner section is directed through the turbine section to drive rotation of the turbine section and a core flow path passes through the burner section and then the turbine section. A condenser assembly is arranged downstream of the turbine section along the core flow path. A cryogenic fuel source is configured to supply fuel to the burner section along a fuel line passing through the condenser assembly and the fuel within the fuel line is configured to pick up heat from the exhaust from the burner section and condense water therefrom.
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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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