公开(公告)号：US20230010158A1

公开(公告)日：2023-01-12

申请号：US17860742

申请日：2022-07-08

Applicant: Raytheon Technologies Corporation

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

IPC: F02C9/40 ,  B64D37/30 ,  B64D37/34 ,  F02C3/22

Abstract: A turbine engine system includes aircraft systems including at least one hydrogen fuel tank, engine systems comprising a compressor section, a combustor section having a burner, and a turbine section, and a hydrogen fuel flow supply line configured to supply hydrogen fuel from the at least one hydrogen fuel tank into the burner for combustion. The turbine engine system has a bypass ratio between 5 to 20.

公开(公告)号：US20220364513A1

公开(公告)日：2022-11-17

申请号：US17321052

申请日：2021-05-14

Applicant: Raytheon Technologies Corporation

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

IPC: F02C7/224

Abstract: An aircraft propulsion systems and aircraft having the same are described. The aircraft propulsion systems have one or more aircraft systems including at least one hydrogen tank and a first heat exchanger and one or more engine systems including at least a main engine core, a second heat exchanger, and a third heat exchanger. The main engine core comprises a compressor section, a combustor section having a burner, and a turbine section. Hydrogen is configured to be supplied from the at least one hydrogen tank through a hydrogen flow path, passing through the first heat exchanger of the aircraft systems, the second heat exchanger of the engine systems, and the third heat exchanger of the engine systems, and then supplied into the burner for combustion.

公开(公告)号：US11939925B2

公开(公告)日：2024-03-26

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 ,  B64D27/10 ,  B64D27/24 ,  B64D31/06 ,  F01D15/10 ,  F02C6/14 ,  F02C9/50 ,  B64D27/02

CPC classification number: F02C7/36 ,  B64D27/10 ,  B64D27/24 ,  B64D31/06 ,  F01D15/10 ,  F02C6/14 ,  F02C9/50 ,  B64D2027/026 ,  F05D2220/76 ,  Y10S903/905 ,  Y10S903/906

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：US20230304439A1

公开(公告)日：2023-09-28

申请号：US17860756

申请日：2022-07-08

Applicant: Raytheon Technologies Corporation

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

IPC: B64D37/34 ,  F02C7/22 ,  F02C7/224 ,  F02C7/228 ,  F02C7/232

CPC classification number: B64D37/34 ,  F02C7/222 ,  F02C7/224 ,  F02C7/228 ,  F02C7/232 ,  B64D2041/005

Abstract: Aircraft propulsion systems and aircraft are described. The 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 an expander, wherein the main engine core comprises 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 expander, prior to being injected into the burner for combustion.

公开(公告)号：US20230257131A1

公开(公告)日：2023-08-17

申请号：US17669955

申请日：2022-02-11

Applicant: Raytheon Technologies Corporation

Inventor： Neil J. Terwilliger ,  Charles E. Lents ,  Zubair A. Baig ,  Haralambos Cordatos ,  Joseph B. Staubach ,  Malcolm P. MacDonald

IPC: B64D33/08 ,  B64D27/24 ,  H05K7/20

CPC classification number: B64D33/08 ,  B64D27/24 ,  H05K7/20372 ,  B64D2221/00

Abstract: A powertrain system of an aircraft includes one or more electrical components to provide electrical power to one or more electrical loads of the aircraft. The system further includes a rechargeable cryogenic heat sink containing a volume of cryogenic cooling material. The cryogenic heat sink is configured to cool the one or more electrical components. A method of operating a powertrain system of an aircraft includes generating thermal energy at one or more electrical components of the powertrain system, fluidly connecting a cryogenic heat sink to the one or more electrical components, and cooling the one or more electrical components via a volume of cryogenic cooling material of the cryogenic heat sink.

公开(公告)号：US11518525B2

公开(公告)日：2022-12-06

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

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.