Modulierter Brennkammer-Bypass

Details

Veröffentlichungs-Nr.

EP3470656

Aktenzeichen

EP18200260

Anmeldetag

12. Oktober 2018

Veröffentlichung

23. Juni 2021

Erteilung

23. Juni 2021

Rechtsraum

EP

IPC

F02K3/02F02C9/18F23R3/02F23R3/26

Abstract

A combustor section (26) of a gas turbine engine (20) includes a combustor (56) having a combustor inlet (62), and a combustor bypass passage (64) having a passage inlet (66) located upstream of the combustor inlet. The combustor bypass passage is configured to divert a selected bypass airflow (70) around the combustor. A combustor bypass valve (72) is located at the combustor bypass passage to control the selected bypass airflow along the combustor bypass passage. A method of operating a gas turbine engine (20), includes urging a core airflow from a compressor section (24) toward a combustor section (26), flowing a first portion of the core airflow into the combustor section via a combustor inlet (62), and flowing a second portion of the core airflow into a combustor bypass passage (64) via a combustor bypass valve (72), thereby bypassing the combustor with the second portion of the core airflow.

Anmelder

Firmen

Raytheon Technologies Corporation
United Technologies Corporation

Land

🇺🇸 USA

Fachgebiete