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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
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.
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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.
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