公开(公告)号：US11725823B2

公开(公告)日：2023-08-15

申请号：US17567533

申请日：2022-01-03

Applicant: Raytheon Technologies Corporation

Inventor： Stephen K. Kramer

IPC: F23R3/60 ,  F23R3/00

CPC classification number: F23R3/60 ,  F23R3/007 ,  F05D2240/35

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：US20240309813A1

公开(公告)日：2024-09-19

申请号：US18121377

申请日：2023-03-14

Applicant: Raytheon Technologies Corporation

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

IPC: F02C7/141 ,  F02C7/16

CPC classification number: F02C7/141 ,  F02C7/16 ,  F05D2240/12 ,  F05D2260/212 ,  F05D2260/2322 ,  F05D2270/16

Abstract: An assembly is provided for a turbine engine. This assembly includes a turbine vane array and a cooling system. The turbine vane array includes an inner platform, an outer platform and a plurality of turbine vanes extending between and connected to the inner platform and the outer platform. The turbine vanes include a first turbine vane, and the first turbine vane includes a first passage and a second passage. The cooling system is configured to direct a first fluid into the first passage and a second fluid into the second passage. The first fluid includes air and steam during a first mode. The second fluid includes the air without the steam during the first mode.

公开(公告)号：US12092023B1

公开(公告)日：2024-09-17

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 ,  F02C7/18 ,  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：US12038177B1

公开(公告)日：2024-07-16

申请号：US18121436

申请日：2023-03-14

Applicant: Raytheon Technologies Corporation

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

IPC: F23R3/14 ,  F02C3/20 ,  F02C3/30 ,  F23R3/28

CPC classification number: F23R3/14 ,  F02C3/20 ,  F02C3/30 ,  F23R3/283

Abstract: An assembly is provided for a turbine engine. This assembly includes a fuel injector assembly, and the fuel injector assembly includes a fuel passage, an air passage and a steam passage. The fuel injector assembly is configured to direct fuel out of the fuel passage along an axis into a volume as a fuel flow. The fuel injector assembly is configured to direct air out of the air passage along the axis into the volume as an air flow, where the air flow circumscribes the fuel flow. The fuel injector assembly is configured to direct steam out of the steam passage along the axis into the volume as a steam flow, where the steam flow circumscribes the fuel flow and provides a radial buffer between the fuel flow and the air flow.

公开(公告)号：US20240159398A1

公开(公告)日：2024-05-16

申请号：US17985863

申请日：2022-11-13

Applicant: Raytheon Technologies Corporation

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

IPC: F23R3/28 ,  F02C7/22

CPC classification number: F23R3/28 ,  F02C7/22

Abstract: An assembly is provided for a gas turbine engine. This engine assembly includes a fuel injector assembly, and the fuel injector assembly includes a fuel swirler and an air swirler. The fuel swirler is configured to swirl fuel in a direction about the axis to provide swirled fuel. The fuel injector assembly is configured to inject the swirled fuel as an annular fuel flow along an axis. The air swirler is configured to swirl air in the direction about the axis to provide swirled air. The fuel injector assembly is configured to inject the swirled air as an annular air flow along the axis, adjacent and circumscribing the annular fuel flow.

公开(公告)号：US11692486B2

公开(公告)日：2023-07-04

申请号：US17843833

申请日：2022-06-17

Applicant: Raytheon Technologies Corporation

Inventor： Stephen K. Kramer ,  Brian Knisely ,  Eric DeShong ,  Shawn Siroka ,  Ivan Monge-Concepcion

IPC: F02C7/16 ,  B22F12/00 ,  F02C3/14 ,  F23R3/00 ,  F23R3/06 ,  B33Y50/00 ,  B22F5/00

CPC classification number: F02C7/16 ,  B22F12/00 ,  F02C3/14 ,  F23R3/002 ,  F23R3/06 ,  B22F2005/005 ,  B33Y50/00 ,  F05D2230/21 ,  F05D2240/35 ,  F23R2900/00018 ,  F23R2900/03044

Abstract: Methods for manufacturing combustor panels of gas turbine engines and combustor panels are described. The methods include defining a particle deposit near-steady state for at least a portion of a combustor panel, the particle deposit near-steady state representative of a build-up of particles on the at least a portion of the combustor panel during use, generating a template based on the defined particle deposit near-steady state, wherein the template includes one or more augmentation elements based on the representative of build-up of particles, and forming a combustor panel based on the template, wherein the formed combustor panel includes one or more augmentation elements defined in the template.

公开(公告)号：US12129788B2

公开(公告)日：2024-10-29

申请号：US18121434

申请日：2023-03-14

Applicant: Raytheon Technologies Corporation

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

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 steam injector. The housing includes an air plenum. The combustor is disposed within the air plenum. The combustor includes a combustor wall and a combustion chamber. The combustor wall is disposed between the combustion chamber and the air plenum. The combustor wall includes a quench aperture that extends through the combustor wall from the air plenum to the combustion chamber. The steam injector projects partially into or through the quench aperture.

公开(公告)号：US20240309810A1

公开(公告)日：2024-09-19

申请号：US18121504

申请日：2023-03-14

Applicant: Raytheon Technologies Corporation

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

IPC: F02C3/30

CPC classification number: F02C3/30 ,  F05D2220/323 ,  F05D2240/12 ,  F05D2260/60

Abstract: An aircraft propulsion system is provided that include a propulsor rotor, a turbine engine core and a steam system. The turbine engine core is configured to power the propulsor rotor. The turbine engine core includes a core flowpath, a compressor section, a combustor section and a turbine section. The core flowpath extends through the compressor section, the combustor section and the turbine section from a flowpath inlet to a flowpath exhaust. The combustor section includes a diffuser plenum and a combustor disposed within the diffuser plenum. The steam system is configured to introduce steam into the core flowpath upstream of the diffuser plenum.

公开(公告)号：US20240309808A1

公开(公告)日：2024-09-19

申请号：US18121434

申请日：2023-03-14

Applicant: Raytheon Technologies Corporation

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

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 steam injector. The housing includes an air plenum. The combustor is disposed within the air plenum. The combustor includes a combustor wall and a combustion chamber. The combustor wall is disposed between the combustion chamber and the air plenum. The combustor wall includes a quench aperture that extends through the combustor wall from the air plenum to the combustion chamber. The steam injector projects partially into or through the quench aperture.

公开(公告)号：US20240302044A1

公开(公告)日：2024-09-12

申请号：US18117920

申请日：2023-03-06

Applicant: Raytheon Technologies Corporation

Inventor： Ian Walters ,  Stephen K. Kramer ,  Gary J. Dillard

IPC: F23R3/28 ,  F23R3/14

CPC classification number: F23R3/286 ,  F23R3/14

Abstract: An assembly is provided for a gas turbine engine. This turbine engine assembly includes a combustor and a fuel injector assembly. The combustor includes a combustion chamber that extends axially along and circumferentially about an axial centerline. The fuel injector assembly is configured to direct fuel and air into the combustion chamber. The fuel injector assembly includes a fuel injector nozzle and an air swirler structure. The fuel injector nozzle projects into and is coupled with the air swirler structure. The centerline axis of at least one of the fuel injector nozzle or the air swirler structure is angularly offset from the axial centerline by an offset angle in a circumferential direction about the axial centerline.