公开(公告)号：US12078104B2

公开(公告)日：2024-09-03

申请号：US18317545

申请日：2023-05-15

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Neil J. Terwilliger ,  Joseph B. Staubach ,  Charles E. Lents

IPC: F02C7/143 ,  F02C3/20 ,  F02C3/22 ,  F02C3/30 ,  F02C7/224 ,  F02C7/22 ,  F02C7/36

CPC classification number: F02C7/1435 ,  F02C3/20 ,  F02C3/22 ,  F02C3/30 ,  F02C3/305 ,  F02C7/143 ,  F02C7/224 ,  F02C7/22 ,  F02C7/36

Abstract: A propulsion system includes a core engine generating a high energy gas flow, a condenser configured to extract water from the high energy gas flow and an evaporator transforming the extracted water into a steam flow. The steam flow is injected into a core flow path of the core engine increase mass flow.

公开(公告)号：US20230374941A1

公开(公告)日：2023-11-23

申请号：US18317545

申请日：2023-05-15

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Neil J. Terwilliger ,  Joseph B. Staubach ,  Charles E. Lents

IPC: F02C7/143 ,  F02C3/22 ,  F02C6/20

CPC classification number: F02C7/1435 ,  F02C3/22 ,  F02C6/20 ,  F05D2260/2322

Abstract: A propulsion system includes a core engine generating a high energy gas flow, a condenser configured to extract water from the high energy gas flow and an evaporator transforming the extracted water into a steam flow. The steam flow is injected into a core flow path of the core engine increase mass flow.

公开(公告)号：US20230011956A1

公开(公告)日：2023-01-12

申请号：US17860215

申请日：2022-07-08

Applicant: Raytheon Technologies Corporation

Inventor： James Wiedenhoefer ,  Joseph B. Staubach ,  Marc J. Muldoon ,  Charles E. Lents ,  Brian M. Holley

IPC: F02C7/224 ,  F02C7/22 ,  F02C3/22

Abstract: A turbine engine system includes at least one hydrogen fuel tank, a core flow path heat exchanger in a core flow path; and engine systems located in the core flow path. The engine system including at least a compressor section, a combustor section having a burner, and a turbine section. The core flow path heat exchanger is arranged in the core flow path downstream of the combustor section. The hydrogen fuel is supplied from the at least one hydrogen fuel tank through a hydrogen fuel supply line, passing through the core flow path heat exchanger and then supplied into the burner for combustion.

公开(公告)号：US20240010351A1

公开(公告)日：2024-01-11

申请号：US17860746

申请日：2022-07-08

Applicant: Raytheon Technologies Corporation

Inventor： Brian M. Holley ,  Joseph B. Staubach ,  Marc J. Muldoon ,  Charles E. Lents

IPC: B64D37/30 ,  B64D41/00 ,  B64D15/12 ,  F02C3/22 ,  F02C7/32

CPC classification number: B64D37/30 ,  B64D41/00 ,  B64D15/12 ,  F02C3/22 ,  F02C7/32 ,  F05D2220/76 ,  F05D2220/323

Abstract: Aircraft propulsion systems include aircraft systems having at least one hydrogen tank and an aircraft-systems heat exchanger and engine systems having 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. 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 includes a rotor separated into a first expander portion and a second expander portion arranged about an output shaft and the output shaft is operably connected to a generator configured to generate electrical power.

公开(公告)号：US20220349351A1

公开(公告)日：2022-11-03

申请号：US17840715

申请日：2022-06-15

Applicant: Raytheon Technologies Corporation

Inventor： Charles E. Lents ,  Joseph B. Staubach ,  Larry W. Hardin ,  Jonathan Rheaume

IPC: F02C7/36 ,  F01D15/10 ,  B64D31/06 ,  F02C6/14 ,  F02C9/50 ,  B64D27/24 ,  B64D27/10

Abstract: A gas turbine engine includes a core having a compressor section with a first compressor and a second compressor, a turbine section with a first turbine and a second turbine, and a primary flowpath fluidly connecting the compressor section and the turbine section. The first compressor is connected to the first turbine via a first shaft, the second compressor is connected to the second turbine via a second shaft, and a motor is connected to the first shaft such that rotational energy generated by the motor is translated to the first shaft. The gas turbine engine includes a takeoff mode of operation, a top of climb mode of operation, and at least one additional mode of operation. The gas turbine engine is undersized relative to a thrust requirement in at least one of the takeoff mode of operation and the top of climb mode of operation, and a controller is configured to control the mode of operation of the gas turbine engine.

公开(公告)号：US11371430B2

公开(公告)日：2022-06-28

申请号：US15200240

申请日：2016-07-01

Applicant: Raytheon Technologies Corporation

Inventor： Charles E. Lents ,  Jonathan Rheaume

IPC: F02C6/14 ,  F02C3/24 ,  F02C3/22 ,  F01D15/10 ,  B64D41/00 ,  F02C7/32 ,  B64D27/24 ,  B64D27/10

Abstract: A gas turbine engine includes a compressor section having a first compressor and a second compressor and a turbine section having a first turbine and a second turbine. The first compressor is connected to the first turbine via a first shaft and the second compressor is connected to the second turbine via a second shaft. A motor connected to the first shaft such that rotational energy generated by the motor is translated to the first shaft. A power distribution system connects the motor to a stored power system including at least one of an energy storage unit and a supplementary power unit. The power distribution system is configured to provide power from the stored power system to the motor.

公开(公告)号：US20240010352A1

公开(公告)日：2024-01-11

申请号：US17860751

申请日：2022-07-08

Applicant: Raytheon Technologies Corporation

Inventor： Brian M. Holley ,  Joseph B. Staubach ,  Marc J. Muldoon ,  Charles E. Lents

IPC: B64D37/30 ,  B64D41/00 ,  B64D37/34 ,  F02C3/22 ,  F02C7/32

CPC classification number: B64D37/30 ,  B64D41/00 ,  B64D37/34 ,  F02C3/22 ,  F02C7/32 ,  F05D2220/323 ,  F05D2260/40311 ,  F05D2220/76

Abstract: 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.

公开(公告)号：US20210380260A1

公开(公告)日：2021-12-09

申请号：US17411529

申请日：2021-08-25

Applicant: Raytheon Technologies Corporation

Inventor： Gabriel L. Suciu ,  Brian Merry ,  Stephen H. Taylor ,  Charles E. Lents

IPC: B64D13/08 ,  F02C6/08 ,  F02C9/18 ,  F02K3/115 ,  B64D27/10 ,  F01D15/10 ,  F02C3/04 ,  F02K3/06 ,  H02K7/18 ,  F02C7/18 ,  F02K3/04

Abstract: An engine driven environmental control system (ECS) air circuit includes a gas turbine engine having a compressor section. The compressor section includes a plurality of compressor bleeds. A selection valve selectively connects each of said bleeds to an input of an intercooler. A second valve is configured to selectively connect an output of said intercooler to at least one auxiliary compressor. The output of each of the at least one auxiliary compressors is connected to an ECS air input.

公开(公告)号：US20230303254A1

公开(公告)日：2023-09-28

申请号：US18082848

申请日：2022-12-16

Applicant: Raytheon Technologies Corporation

Inventor： Frederick M. Schwarz ,  Michael Winter ,  Charles E. Lents ,  Nathan Snape ,  Alan H. Epstein

IPC: B64D13/08 ,  F02C7/141 ,  F02C7/16 ,  F02C9/18 ,  F25B9/14 ,  F25J3/04 ,  B01D45/08 ,  B01D53/00 ,  B03C1/28 ,  B64D27/12 ,  B64D33/08 ,  F01D15/00 ,  F01D25/12 ,  F02C6/08 ,  F02C7/143 ,  F02C7/18 ,  F02K3/06 ,  B64D13/06 ,  F17C7/02 ,  F17C7/04

CPC classification number: B64D13/08 ,  F02C7/141 ,  F02C7/16 ,  F02C9/18 ,  F25B9/14 ,  F25J3/04254 ,  B01D45/08 ,  B01D53/002 ,  B03C1/288 ,  B64D27/12 ,  B64D33/08 ,  F01D15/00 ,  F01D25/12 ,  F02C6/08 ,  F02C7/143 ,  F02C7/185 ,  F02K3/06 ,  F25J3/04975 ,  B64D13/06 ,  F17C7/02 ,  F17C7/04 ,  B64D37/32

Abstract: A gas turbine engine includes a compressor section and a turbine section operably coupled to the compressor section. The gas turbine engine further includes a means for selectively releasing a cooling fluid flow produced at a cryogenic temperature and a plumbing system in fluid communication with the means for selectively releasing the cooling fluid flow. The plumbing system is configured to route the cooling fluid flow to one or more of the compressor section and the turbine section.

公开(公告)号：US20230122852A1

公开(公告)日：2023-04-20

申请号：US18082888

申请日：2022-12-16

Applicant: Raytheon Technologies Corporation

Inventor： Frederick M. Schwarz ,  Michael Winter ,  Charles E. Lents ,  Nathan Snape ,  Alan H. Epstein

IPC: B64D13/08 ,  F02C7/141 ,  F02C7/16 ,  F02C9/18 ,  F25B9/14 ,  F25J3/04 ,  B01D45/08 ,  B01D53/00 ,  B03C1/28 ,  B64D27/12 ,  B64D33/08 ,  F01D15/00 ,  F01D25/12 ,  F02C6/08 ,  F02C7/143 ,  F02C7/18 ,  F02K3/06 ,  B64D13/06 ,  F17C7/02 ,  F17C7/04

Abstract: An engine-driven cryogenic cooling system for an aircraft includes a first air cycle machine, a second air cycle machine, and a means for condensing a chilled air stream into liquid air for an aircraft use. The first air cycle machine includes a plurality of components operably coupled to a gearbox of a gas turbine engine and configured to produce a cooling air stream based on a first engine bleed source of the gas turbine engine. The second air cycle machine is operable to output the chilled air stream at a cryogenic temperature based on a second engine bleed source cooled by the cooling air stream of the first air cycle machine.