公开(公告)号：US20240302042A1

公开(公告)日：2024-09-12

申请号：US18117924

申请日：2023-03-06

Applicant: Raytheon Technologies Corporation

Inventor： Ian Walters ,  Stephen K. Kramer ,  Baris A. Sen ,  Gary J. Dillard ,  Eunice Allen-Bradley

IPC: F23R3/00

CPC classification number: F23R3/002

Abstract: An apparatus is provided for a turbine engine. This turbine engine apparatus includes a combustor wall, and the combustor wall includes a panel, a deflector and a quench aperture that extends along an aperture centerline through the combustor wall to an aperture outlet into a combustion chamber. The panel extends axially along and circumferentially about an axis. The panel extends radially between a first panel side and a second panel side. The first panel side forms a peripheral boundary of the combustion chamber. The panel forms a downstream side of the aperture outlet at the first panel side. The deflector projects out from the panel at the first panel side into the combustion chamber. The deflector forms an upstream side of the aperture outlet.

公开(公告)号：US20240288169A1

公开(公告)日：2024-08-29

申请号：US18114691

申请日：2023-02-27

Applicant: Raytheon Technologies Corporation

Inventor： Baris A. Sen ,  Andrew W. Justice ,  Stephen K. Kramer ,  Gary J. Dillard

IPC: F23R3/28 ,  F02C7/232

CPC classification number: F23R3/286 ,  F02C7/232 ,  F05D2220/32 ,  F05D2240/36

Abstract: An assembly is provided for a turbine engine. This turbine engine assembly includes an air swirler structure, an injector nozzle and a nozzle guide. The air swirler structure includes a swirler wall, an inner passage and an air swirler passage. The swirler wall includes a flow guide surface. At least an inner portion of the flow guide surface has a frustoconical geometry. The inner passage extends axially along an axis within the air swirler structure to a swirler outlet. The air swirler passage extends radially into the air swirler structure, longitudinally along the flow guide surface and to the inner passage. The injector nozzle projects axially into the inner passage. The nozzle guide couples the injector nozzle to the air swirler structure. The nozzle guide is axially abutted against the swirler wall.

公开(公告)号：US20210317785A1

公开(公告)日：2021-10-14

申请号：US16844683

申请日：2020-04-09

Applicant: Raytheon Technologies Corporation

Inventor： Enzo DiBenedetto ,  Anthony R. Bifulco ,  William K. Ackermann ,  Paul E. Coderre ,  John H. Mosley ,  Stephen K. Kramer

IPC: F02C7/18 ,  F01D25/12

Abstract: A cooling system includes an inlet, a passageway, and a feed passage. The inlet is defined by a strut of a diffuser case that extends between a first case portion and a second case portion. The inlet extends from a leading surface towards a trailing surface along a first axis. The passageway is defined by the strut and extends from the inlet towards the second case portion along a second axis that is disposed transverse to the first axis. The feed passage is defined between a body of a tangential onboard injection system that extends between and is connected to an inner vane platform of a guide vane and the second case portion. The feed passage extends along an axis that is disposed parallel to the first axis.

公开(公告)号：US12163466B2

公开(公告)日：2024-12-10

申请号：US18121442

申请日：2023-03-14

Applicant: Raytheon Technologies Corporation

Inventor： Stephen K. Kramer ,  Zhongtao Dai ,  Lance L. Smith ,  Gregory Boardman

IPC: F02C3/30

Abstract: An assembly is provided for a turbine engine. This assembly includes a housing, a combustor and a fuel injector assembly. The housing includes a case and a diffuser plenum radially within the case. The case extends axially along and circumferentially about a centerline. The combustor is disposed within the diffuser plenum. The combustor includes a bulkhead, a hood, a combustion chamber and a hood cavity. The bulkhead is axially between the combustion chamber and the hood cavity. The hood is between the hood cavity and the diffuser plenum. The fuel injector assembly projects radially into the diffuser plenum from the case. The fuel injector assembly includes a fuel nozzle and a steam nozzle. The fuel nozzle is configured to inject fuel into the combustion chamber. The steam nozzle is configured to inject steam into the hood cavity.

公开(公告)号：US12007115B1

公开(公告)日：2024-06-11

申请号：US18115111

申请日：2023-02-28

Applicant: Raytheon Technologies Corporation

Inventor： Baris A. Sen ,  Zhongtao Dai ,  Wookyung Kim ,  Stephen K. Kramer

IPC: F23R3/14

CPC classification number: F23R3/14

Abstract: A fuel injector assembly for a gas turbine engine includes a swirler and a fuel nozzle. The swirler has an outer wall having a SOW inner wall surface, an inner wall having a SIW inner wall surface and a SIW outer wall surface, an outer passage, and an inner passage. The SIW inner wall surface includes first and second sections. The first section extends between a first airflow inlet and the second section, and the second section extends between the first section and an inner wall distal end. The first section tapers radially inward, and the second section extends parallel the center axis. The outer wall circumscribes the inner wall and extends axially along the center axis to a distal outer wall end, and the distal end wall is axially recessed within the swirler from the distal outer wall end. The fuel nozzle projects into the inner passage.

公开(公告)号：US20220275942A1

公开(公告)日：2022-09-01

申请号：US17567533

申请日：2022-01-03

Applicant: Raytheon Technologies Corporation

Inventor： Stephen K. Kramer

IPC: F23R3/60 ,  F23R3/00

Abstract: A combustor with a centerline is provided that includes a support structure and a heat shield. The heat shield extends circumferentially about and axially along the centerline. The heat shield is configured from or otherwise includes ceramic material. The heat shield is mounted to the support structure by an interlocking joint connection. The interlocking joint connection includes a projection and a groove. The projection is configured with the support structure and includes a plurality of fingers arranged along and projecting into the groove. The groove is formed in the heat shield.

公开(公告)号：US20240309811A1

公开(公告)日：2024-09-19

申请号：US18121503

申请日：2023-03-14

Applicant: Raytheon Technologies Corporation

Inventor： Stephen K. Kramer ,  Lance L. Smith ,  Zhongtao Dai ,  Gregory Boardman

IPC: F02C3/30 ,  F23R3/10

CPC classification number: F02C3/305 ,  F02C3/30 ,  F02C7/18 ,  F23R3/10 ,  F23R2900/03044

Abstract: An assembly is provided for a turbine engine. This assembly includes a housing, a combustor and a steam system. The housing includes an air plenum. The combustor is disposed within the air plenum. The combustor includes a combustion chamber and a combustor wall between the combustion chamber and the air plenum. The steam system includes a steam injector arranged within the air plenum next to the combustor wall. The steam system is configured to inject steam out of the steam injector and into the air plenum to impinge against the combustor wall.

公开(公告)号：US20240309809A1

公开(公告)日：2024-09-19

申请号：US18121442

申请日：2023-03-14

Applicant: Raytheon Technologies Corporation

Inventor： Stephen K. Kramer ,  Zhongtao Dai ,  Lance L. Smith ,  Gregory Boardman

IPC: F02C3/30

CPC classification number: F02C3/30 ,  F05D2220/32 ,  F05D2240/35 ,  F05D2270/08

Abstract: An assembly is provided for a turbine engine. This assembly includes a housing, a combustor and a fuel injector assembly. The housing includes a case and a diffuser plenum radially within the case. The case extends axially along and circumferentially about a centerline. The combustor is disposed within the diffuser plenum. The combustor includes a bulkhead, a hood, a combustion chamber and a hood cavity. The bulkhead is axially between the combustion chamber and the hood cavity. The hood is between the hood cavity and the diffuser plenum. The fuel injector assembly projects radially into the diffuser plenum from the case. The fuel injector assembly includes a fuel nozzle and a steam nozzle. The fuel nozzle is configured to inject fuel into the combustion chamber. The steam nozzle is configured to inject steam into the hood cavity.

公开(公告)号：US20240308680A1

公开(公告)日：2024-09-19

申请号：US18120828

申请日：2023-03-13

Applicant: Raytheon Technologies Corporation

Inventor： Gregory Boardman ,  Stephen K. Kramer

IPC: B64D37/16 ,  B64D37/06 ,  B64D37/30 ,  F02M37/00

CPC classification number: B64D37/16 ,  B64D37/06 ,  B64D37/30 ,  F02M37/0088

Abstract: During a method, an aircraft powerplant is provided. The aircraft powerplant includes an injector and a fuel system configured to deliver fuel to the injector. The fuel system includes a first tank, a first circuit and a second circuit arranged in parallel with the first circuit between the first tank and the injector. The second circuit includes a second tank. The fuel is directed from the first tank to the injector during a first mode through the first circuit and independent of the second circuit. The fuel is directed from the second tank to the injector during a second mode through the second circuit and independent of the first circuit.

公开(公告)号：US20240271784A1

公开(公告)日：2024-08-15

申请号：US18110186

申请日：2023-02-15

Applicant: Raytheon Technologies Corporation

Inventor： Orin G. Avidane ,  Andre M. Ajami ,  Coy Bruce Wood ,  Joseph V. Mantese ,  David L. Lincoln ,  Stephen K. Kramer ,  Ramesh Rajagopalan

IPC: F23N5/08 ,  F23N1/00 ,  F23R3/28

CPC classification number: F23N5/082 ,  F23N1/005 ,  F23R3/28 ,  F23N2229/04 ,  F23N2229/16 ,  F23N2229/18

Abstract: A combustion assembly for a gas turbine engine includes a combustor, a monochromator, and a photodetector assembly. The combustor forms a combustion chamber. The monochromator is disposed outside the combustion chamber. The monochromator is configured to receive an optical input from the combustion chamber and direct an optical output. The optical input has a range of light wavelengths. The optical output has a subset of the range of light wavelengths. The photodetector assembly is disposed outside the combustion chamber. The photodetector assembly is configured to receive the optical output from the monochromator and generate an output signal representative of one or more optical characteristics of the optical output.