公开(公告)号：US20210003282A1

公开(公告)日：2021-01-07

申请号：US16846849

申请日：2020-04-13

Applicant: Raytheon Technologies Corporation

Inventor： Torence P. Brogan ,  Jeffery A. Lovett ,  Christopher A. Eckett ,  May L. Corn

IPC: F23R3/28 ,  F23R3/20

Abstract: A fuel injection system for a gas turbine engine includes a fuel delivery conduit, a nozzle block with a nozzle aperture, and a cavity block with a cavity. The nozzle aperture has a first cross sectional area, and injects fuel received from the fuel delivery conduit into the cavity. The cavity has a second cross sectional area that is greater than the first cross sectional area.

公开(公告)号：US11085400B2

公开(公告)日：2021-08-10

申请号：US16254889

申请日：2019-01-23

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Christopher A. Eckett ,  Gabriel L. Suciu

IPC: F02K3/075 ,  F02K1/72 ,  F02K3/06 ,  F02K1/76 ,  F02K1/09 ,  B64D27/26 ,  B64D29/06 ,  B64D33/04 ,  F01D25/24 ,  F02C3/04 ,  F02K1/70

Abstract: An integrated propulsion system according to an example of the present disclosure includes, among other things, components that include a gas turbine engine, a nacelle assembly and a mounting assembly, the system designed by a process comprising identifying two or more of internal structural loading requirements, external structural mount loading requirements, aerodynamic requirements, and acoustic requirements for the system, and interdependently designing said components to meet said requirements. The nacelle assembly includes a fan nacelle and an aft nacelle, the fan nacelle arranged at least partially about a fan and the engine, and the fan nacelle arranged at least partially about a core cowling to define a bypass flow path.

公开(公告)号：US20240026827A1

公开(公告)日：2024-01-25

申请号：US18091860

申请日：2022-12-30

Applicant: Raytheon Technologies Corporation

Inventor： Steven W. Burd ,  Christopher A. Eckett

IPC: F02C7/32 ,  F02C3/073 ,  F02C3/113 ,  F02C3/14 ,  F02C6/18

CPC classification number: F02C7/32 ,  F02C3/073 ,  F02C3/113 ,  F02C3/14 ,  F02C6/18 ,  F05D2220/323 ,  F05D2220/50

Abstract: An aircraft system is provided that includes a gas turbine engine, a gearbox and at least one compressor. The gas turbine engine includes a compressor section, a turbine section, a combustor section and a rotating structure. The combustor section is fluidly coupled with and between the compressor section and the turbine section. The rotating structure includes a compressor section rotor within the compressor section and a turbine section rotor within the turbine section. The at least one compressor includes a compressor rotor rotatably driven by the rotating structure through the gearbox. The gas turbine engine may be dedicated to powering the at least one compressor.

公开(公告)号：US12215628B2

公开(公告)日：2025-02-04

申请号：US18091860

申请日：2022-12-30

Applicant: Raytheon Technologies Corporation

Inventor： Steven W. Burd ,  Christopher A. Eckett

IPC: F02C7/32 ,  F02C3/073 ,  F02C3/10 ,  F02C3/113 ,  F02C3/14 ,  F02C6/18 ,  F02C6/20 ,  F02C7/36 ,  F02K3/06

Abstract: An aircraft system is provided that includes a gas turbine engine, a gearbox and at least one compressor. The gas turbine engine includes a compressor section, a turbine section, a combustor section and a rotating structure. The combustor section is fluidly coupled with and between the compressor section and the turbine section. The rotating structure includes a compressor section rotor within the compressor section and a turbine section rotor within the turbine section. The at least one compressor includes a compressor rotor rotatably driven by the rotating structure through the gearbox. The gas turbine engine may be dedicated to powering the at least one compressor.

公开(公告)号：US11661906B2

公开(公告)日：2023-05-30

申请号：US17371672

申请日：2021-07-09

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Christopher A. Eckett ,  Gabriel L. Suciu

IPC: F02K3/075 ,  F02K1/72 ,  F02K3/06 ,  F02K1/76 ,  F02K1/09 ,  B64D27/26 ,  B64D29/06 ,  B64D33/04 ,  F01D25/24 ,  F02C3/04 ,  F02K1/70

CPC classification number: F02K3/075 ,  B64D27/26 ,  B64D29/06 ,  B64D33/04 ,  F01D25/24 ,  F02C3/04 ,  F02K1/09 ,  F02K1/72 ,  F02K1/763 ,  F02K3/06 ,  B64D2027/266 ,  B64D2027/268 ,  F02K1/70 ,  F05D2240/14 ,  F05D2270/051 ,  Y02T50/60

Abstract: An integrated propulsion system according to an example of the present disclosure includes, among other things, a fan section, a gas turbine engine, a geared architecture, a nacelle assembly and a mounting assembly. The nacelle assembly includes a fan nacelle and an aft nacelle, the fan nacelle arranged at least partially about a fan and the engine, and the fan nacelle arranged at least partially about a core cowling to define a bypass flow path.