Kühlluft Zwischenkühlung mit Doppeldurchgangswärmetauscher

Details

Veröffentlichungs-Nr.

EP3085923

Aktenzeichen

EP16166707

Anmeldetag

22. April 2016

Veröffentlichung

27. Mai 2020

Erteilung

27. Mai 2020

Rechtsraum

EP

IPC

F02C3/13F02C7/143F02C7/18

Abstract

A gas turbine engine (100) comprises a main compressor section having a downstream most end (82), and more upstream locations. A turbine section has a high pressure turbine (117). A tap (110) taps air from at least one of the more upstream locations in the compressor section, passes the tapped air through a heat exchanger (112) and then to a cooling compressor (114). The cooling compressor (114) compresses air downstream of the heat exchanger (112), and delivers air into the high pressure turbine (117). The heat exchanger (112) has at least two passes, with one of the passes passing air radially outwardly, and a second of the passes returning the air radially inwardly to the compressor (114). An intercooling system for a gas turbine engine (100) is also disclosed.

Anmelder

Firmen

Raytheon Technologies Corporation
United Technologies Corporation

Land

🇺🇸 USA

Fachgebiete