公开(公告)号：US20240280050A1

公开(公告)日：2024-08-22

申请号：US18171092

申请日：2023-02-17

Applicant: Raytheon Technologies Corporation

Inventor： Marc J. Muldoon ,  William K. Ackermann ,  Anthony R. Bifulco

IPC: F02C6/08 ,  F01D9/02

CPC classification number: F02C6/08 ,  F01D9/02 ,  F05D2220/323 ,  F05D2240/126 ,  F05D2260/60

Abstract: A gas turbine engine includes a compressor section having a downstream most location and more upstream locations. A compressor housing surrounds the compressor rotors. A combustor is downstream of the compressor and a turbine section is downstream of the combustor. At least one bleed inlet passage bleeds air compressed from the compressor section, and delivers the air for use on an associated aircraft. A baffle plate is intermediate the at least one bleed inlet passage and a bleed exit port from the gas turbine engine. The baffle plate has a plurality of holes for allowing the air to flow from the bleed inlet passage to the bleed exit port, with an area of the holes increasing from a location adjacent the at least one bleed inlet passage and in a circumferential direction away from the at least one bleed inlet passage. An aircraft air supply system and an aircraft are also disclosed.

公开(公告)号：US20240262515A1

公开(公告)日：2024-08-08

申请号：US18163676

申请日：2023-02-02

Applicant: Raytheon Technologies Corporation ,  Rohr, Inc.

Inventor： Marc J. Muldoon ,  Murat Yazici ,  Brian Sherman

IPC: B64D27/24 ,  B64D15/12 ,  B64D27/10 ,  B64D29/00 ,  F02C6/14

CPC classification number: B64D27/24 ,  B64D15/12 ,  B64D27/10 ,  B64D29/00 ,  F02C6/14 ,  B64D27/026

Abstract: A propulsion system of an aircraft includes a hybrid electric gas turbine engine, and a nacelle at least partially enclosing the hybrid electric gas turbine engine. The nacelle includes a first nacelle half and a second nacelle half. Each of the first nacelle half and the second nacelle half include an outer nacelle sleeve, an inner nacelle sleeve radially offset from the outer nacelle sleeve such that a flowpath is defined between the outer nacelle sleeve and the inner nacelle sleeve, and an upper bifurcation connecting the outer nacelle sleeve to the inner nacelle sleeve at an upper end of the nacelle. The flowpath is circumferentially continuous between the upper bifurcation of the first nacelle half and the upper bifurcation of the second nacelle half.

公开(公告)号：US11859910B2

公开(公告)日：2024-01-02

申请号：US17320853

申请日：2021-05-14

Applicant: Raytheon Technologies Corporation

Inventor： Joseph B. Staubach ,  Marc J. Muldoon ,  James F. Wiedenhoefer

IPC: F28F9/013 ,  F28D1/047 ,  F02C1/04 ,  F28F1/02 ,  F28F9/02 ,  F28D1/02 ,  F28D21/00

CPC classification number: F28D1/0475 ,  F02C1/04 ,  F28F1/025 ,  F28F9/013 ,  F28F9/0131 ,  F28F9/0221 ,  F05D2220/32 ,  F05D2260/20 ,  F28D2001/028 ,  F28D2001/0273 ,  F28D2021/004 ,  F28D2021/0026

Abstract: A heat exchanger for heat exchange between a first fluid and a second fluid has a plurality of tube sections, each having; an interior for passing the first fluid; an exterior for exposure to the second fluid; a first leg; a second leg; and a turn joining the first leg to the second leg. A has: fiber members passing between legs of the tube sections; and an end plate.

公开(公告)号：US20230220785A1

公开(公告)日：2023-07-13

申请号：US17967369

申请日：2022-10-17

Applicant: Raytheon Technologies Corporation

Inventor： Marc J. Muldoon ,  Russell B. Witlicki

IPC: F01D25/16

CPC classification number: F01D25/16 ,  F05D2220/76 ,  F05D2220/323 ,  F05D2240/54

Abstract: An assembly is provided for a turbine engine. This turbine engine assembly includes a rotating structure, a stationary structure, a bearing and a gearbox. The rotating structure is configured to rotate about a rotational axis. The rotating structure includes a shaft and a bladed rotor connected to the shaft. The stationary structure circumscribes the rotating structure. The bearing rotatably mounts the shaft to the stationary structure. The gearbox is disposed radially inboard of the bearing.

公开(公告)号：US20230212959A1

公开(公告)日：2023-07-06

申请号：US17967460

申请日：2022-10-17

Applicant: Raytheon Technologies Corporation

Inventor： Marc J. Muldoon ,  Russell B. Witlicki

IPC: F01D25/18 ,  F01D25/16 ,  F02C6/20

CPC classification number: F01D25/183 ,  F01D25/16 ,  F02C6/20 ,  F05D2220/70 ,  F05D2220/323 ,  F05D2240/54 ,  F05D2240/55 ,  F05D2260/98

Abstract: An assembly is provided for a turbine engine. This turbine engine assembly includes a first rotating structure, a turbine engine apparatus, a rotating coupler and a seal assembly. The first rotating structure is configured to rotate about a rotational axis. The turbine engine apparatus includes an electric machine and a second rotating structure. The electric machine includes an electric machine rotor and an electric machine stator. The second rotating structure is configured to rotate about the rotational axis and is coupled to the electric machine rotor. The rotating coupler is coupled to the first rotating structure by a first connection. The rotating coupler is coupled to the second rotating structure by a second connection. The seal assembly includes a rotating seal land and a stationary seal element. The rotating seal land is mounted onto the rotating coupler. The stationary seal element sealingly engages the rotating seal land.

公开(公告)号：US11661889B1

公开(公告)日：2023-05-30

申请号：US17581375

申请日：2022-01-21

Applicant: Raytheon Technologies Corporation

Inventor： Marc J. Muldoon ,  Joseph B. Staubach

IPC: F02C7/18 ,  F02C3/22 ,  F02C7/141 ,  F02C5/02

CPC classification number: F02C7/18 ,  F02C3/22 ,  F02C5/02 ,  F02C7/141 ,  F05D2220/323 ,  F05D2240/35 ,  F05D2250/312 ,  F05D2260/213 ,  F05D2260/232

Abstract: Aircraft propulsion systems include a fan shaft connected to a fan, the fan shaft defining a centerline axis of the aircraft propulsion system, one or more offset cores arranged at an angle to the centerline axis, the one or more offset cores each comprising a hydrogen burning combustor, a centerline cavity defined along the centerline axis, and a heat exchanger arranged within the centerline cavity. In operation, a portion of air is directed from the fan into the centerline cavity to provide a first working fluid to the heat exchanger within the centerline cavity.

公开(公告)号：US20230056571A1

公开(公告)日：2023-02-23

申请号：US17512824

申请日：2021-10-28

Applicant: Raytheon Technologies Corporation

Inventor： Marc J. Muldoon ,  Michael E. McCune ,  Keith B. Allyn

IPC: F01D25/28 ,  F01D9/02 ,  F01D25/24

Abstract: A gear reduction reduces a speed of a fan rotor relative to a speed of a fan drive turbine. A rigid connection between a fan case and an inner core housing includes a plurality of A-frames connected at a connection point to the fan case. Legs in the A-frames extend away from the connection point in opposed circumferential directions to be connected to a compressor wall of the inner core housing. The rigid connection also includes a plurality of fan exit guide vanes rigidly connected to the fan case. A lateral stiffness ratio of the lateral stiffness of the plurality of fan exit guide vanes and a lateral stiffness of a combination of the plurality of A-frame, the compressor wall, and a fan intermediate case which is forward of the low pressure compressor being greater than or equal to 0.6 and less than or equal to 2.0.

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：US20220397064A1

公开(公告)日：2022-12-15

申请号：US17837829

申请日：2022-06-10

Applicant: Raytheon Technologies Corporation

Inventor： Marc J. Muldoon ,  Arnab Roy ,  John R. Farris

IPC: F02C7/32 ,  B64D27/24 ,  B64D27/16 ,  F02C6/14

Abstract: A hybrid electric propulsion system including: a gas turbine engine comprising a low speed spool and a high speed spool, the low speed spool comprising a low pressure compressor and a low pressure turbine, and the high speed spool comprising a high pressure compressor and a high pressure turbine; an electric motor configured to augment rotational power of the high speed spool or the low speed spool; at least one blade outer air seal positioned between an outer case of the high pressure turbine and a plurality of blades of the high pressure turbine; a clearance control system operably coupled to the at least one blade outer air seal, the clearance control system configured to vary a position of the at least one blade outer air seal with respect to the plurality of blades of the high pressure turbine; and a controller operably coupled to the electric motor and the clearance control system, wherein the controller is configured to operate the clearance control system based upon an operational state of the electric motor.

公开(公告)号：US20220082052A1

公开(公告)日：2022-03-17

申请号：US17018795

申请日：2020-09-11

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Marc J. Muldoon ,  Jonathan Rheaume ,  Stephen H. Taylor

IPC: F02C7/18

Abstract: An ejector assembly for a cooling system of a gas turbine engine may comprise: a tail cone having a tail cone outlet in fluid communication with a cooling air flow of the cooling system; an ejector body defining a mixing section, a constant area section, and a diffuser section; and a nozzle section in fluid communication with an exhaust air flow of the gas turbine engine, the ejector assembly configured to entrain the cooling air flow via the exhaust air flow.