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.