Zwischengekühlte Kühlluft mit Fortschrittlichem Kühlsystem

Details

Veröffentlichungs-Nr.

EP3557030

Aktenzeichen

EP19170209

Anmeldetag

18. April 2019

Veröffentlichung

23. Februar 2022

Erteilung

23. Februar 2022

Rechtsraum

EP

IPC

F02C7/18F02C9/18

Abstract

A gas turbine engine (20) includes a plurality of rotatable components housed within a compressor section (102) and a turbine section (28). A tap (104) is connected to a location upstream of a downstream most location (105) in the compressor section (102). The tap (104) is connected to a heat exchanger (116). Downstream of the heat exchanger (116) is a shut off valve (118) and downstream of the shut off valve (118) is a cooling compressor (120). The cooling compressor (120) is connected to deliver cooling air through a chamber (133; 144), and then to at least one of the plurality of rotatable components. The chamber (133; 144) is provided with at least one check valve (134; 146) configured to selectively allow flow directly from a more downstream location in the compressor section (102) than the location upstream. The flow from the more downstream location has a higher pressure than a flow from the location upstream. There is a system for stopping operation of the cooling compressor (120). There is a control (126) for closing the shut off valve (118). The cooling compressor (120) is configured to compress air to a greater pressure than the higher pressure, such that when the cooling compressor (120) is providing air, the at least one check valve (134; 146) is configured to maintain a closed position, but when said cooling compressor (120) is not providing compressed air, the at least one check valve (134; 146) is configured to allow said higher pressure flow into said chamber (133; 144). A method is also disclosed.

Anmelder

Firmen

Raytheon Technologies Corporation
United Technologies Corporation

Land

🇺🇸 USA

Fachgebiete