Gasturbinentriebwerk

Details

Veröffentlichungs-Nr.

EP3327276

Aktenzeichen

EP17199655

Anmeldetag

2. November 2017

Veröffentlichung

27. Februar 2019

Erteilung

27. Februar 2019

Rechtsraum

EP

IPC

F02K3/08F02C7/36F02C3/14

Abstract

A gas turbine engine (10) comprises a high pressure compressor (18) coupled to a high pressure turbine (22) by a high pressure shaft (38), a core combustor (20) located downstream of the high pressure compressor (18) and upstream of the high pressure turbine (22), and a low pressure compressor (14) provided upstream of the high pressure compressor (18). The low pressure compressor (14) is configured to direct core airflow to the high pressure compressor (18) and first bypass airflow which bypasses the high pressure compressor (18), core combustor (20) and high pressure turbine (22) through a first bypass duct (24). The engine (10) further comprises a mixer (26) downstream of the high pressure turbine (22) and low pressure compressor (14), the mixer (26) being configured to mix the core and first bypass airflows. The engine also comprises a re-heat combustor (28) configured to combust fuel with both core airflow and first bypass airflow. A low pressure turbine (30) is provided downstream of the re-heat combustor (28) and coupled to the low pressure compressor (14) by a low pressure shaft (36), the low pressure and high pressure shafts (38, 36) being independently rotatable. A shaft power transfer arrangement (40) is provided, which is configured to selectively transfer power between the low pressure and high pressure shafts (36, 38).

Anmelder

Firma

Rolls-Royce plc

Land

🇬🇧 Großbritannien

Fachgebiete