Zwischengekühlte Kühlluft

Details

Veröffentlichungs-Nr.

EP3533988

Aktenzeichen

EP19160126

Anmeldetag

28. Februar 2019

Veröffentlichung

2. Juni 2021

Erteilung

2. Juni 2021

Rechtsraum

EP

IPC

F02K3/04F02C6/08F02C7/18

Abstract

A gas turbine engine (201) includes a plurality of rotating components housed within a compressor section and a turbine section. A first tap (156) is connected to the compressor section and configured to deliver air at a first pressure. A heat exchanger (158) is connected downstream of the first tap (156) and configured to deliver air to an aircraft fuselage (152). A cooling compressor (164) is connected downstream of the heat exchanger (158). A high pressure feed (200) is configured to deliver air at a second pressure which is higher than the first pressure. The cooling compressor (164) is configured to deliver air to at least one of the plurality of rotating components. A valve assembly (202) can select whether air from the first tap (156) or air from the high pressure feed (200) is delivered to the aircraft fuselage (152).

Anmelder

Firmen

Raytheon Technologies Corporation
United Technologies Corporation

Land

🇺🇸 USA

Fachgebiete