Aufgeladene Brennkammerkühlung mit Turbomaschinen

Details

Veröffentlichungs-Nr.

EP4647666

Aktenzeichen

EP25175857

Anmeldetag

12. Mai 2025

Veröffentlichung

12. November 2025

Rechtsraum

EP

IPC

F23R3/54F02C3/14F02C7/224F23R3/06

Abstract

A gas turbine engine (100a) includes a compressor (102), a combustor (104) downstream of the compressor (102), a turbine (108) downstream of the combustor (104), and a shaft (110) mechanically connecting the turbine (108) and the compressor (102). The combustor (104) is fluidically connected to the compressor (102) to receive a first portion of the compressed air as combustor primary inlet air (130a). The combustor (104) includes a combustor liner (140) having an inner combustor liner (140a) and an outer combustor liner (140b), surrounding one or more combustion zones. A cooling air flow path (124) is configured to direct a second portion (130b) of the compressed air around the outer combustor liner (140b) to cool the combustor liner (140) and to provide a source of quench air (130d; 130h), inner combustor liner cooling air (130g), fuel injector air (130i; 130j), and combustor secondary inlet air (130k).

Anmelder

Firma

RTX Corporation

Land

🇺🇸 USA

Fachgebiete