公开(公告)号：US20240255146A1

公开(公告)日：2024-08-01

申请号：US18104685

申请日：2023-02-01

Applicant: RTX Corporation

Inventor： Ian Walters ,  Baris A. Sen ,  Manuel J. Hernandez ,  Scott A. Liljenberg ,  Stephen K. Kramer

IPC: F23R3/06 ,  F23R3/00

CPC classification number: F23R3/06 ,  F23R3/002

Abstract: A wall assembly for use in a combustor of a gas turbine engine, the wall assembly including: a support shell; a liner panel; and an annular grommet extending from the liner panel, the annular grommet defining a dilution passage and the annular grommet extends through an opening in the support shell when the support shell and the liner panel are secured to each other, the annular grommet having a top portion that defines a portion of a periphery of the dilution opening; and a backstop extending from the top portion of the annular grommet, the backstop defining another portion of the periphery of the dilution passage and the backstop extending through and above the opening in the support shell when the liner panel is secured to the support shell.

公开(公告)号：US20250020078A1

公开(公告)日：2025-01-16

申请号：US18899997

申请日：2024-09-27

Applicant: RTX Corporation

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

IPC: F02C3/30

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：US20240255147A1

公开(公告)日：2024-08-01

申请号：US18428580

申请日：2024-01-31

Applicant: RTX Corporation

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

IPC: F23R3/14 ,  F23R3/28

CPC classification number: F23R3/14 ,  F23R3/28

Abstract: An assembly is provided for a gas turbine engine. This assembly includes an air swirler structure, an injector nozzle and a nozzle guide. The air swirler structure includes an inner bore and an air swirler passage. The inner bore extends axially along an axis through the air swirler structure. The air swirler passage extends radially into the air swirler structure to the inner bore. The injector nozzle projects axially into the inner bore. The nozzle guide couples the injector nozzle to the air swirler structure. The nozzle guide includes a guide foot and an air purge passage radially outboard of the guide foot. The guide foot is configured to radially engage the injector nozzle. The air purge passage extends across the nozzle guide and axially to the inner bore.

公开(公告)号：US20240328624A1

公开(公告)日：2024-10-03

申请号：US18738916

申请日：2024-06-10

Applicant: RTX 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.