An der Rückseite eines Gasturbinentriebwerks Montierter Wärmetauscher für Anspruchsvolle Temperaturanwendungen

Details

Veröffentlichungs-Nr.

EP3330524

Aktenzeichen

EP17205089

Anmeldetag

4. Dezember 2017

Veröffentlichung

22. März 2023

Erteilung

22. März 2023

Rechtsraum

EP

IPC

F02K3/115F02C7/141F02C9/18

Abstract

A gas turbine engine (100) has a fan rotor (87) delivering air into a bypass duct defined between an outer fan case (94) and an outer interior housing. The fan rotor (87) also delivers air into a compressor section (77,79), a combustor (106), a turbine section (108H,108L). A chamber (97) is defined between the outer interior housing and an inner housing (113). The inner housing (113) contains the compressor section (77,79), the combustor (106) and the turbine section (108H,108L). A first conduit (110) taps hot compressed air to be cooled and passes the air to at least one heat exchanger (102). The air is cooled in the heat exchanger (102) and returned to a return conduit (112). The return conduit (112) passes the cooled air to at least one of the turbine section (108H,108L) and the compressor section (77,79). The heat exchanger (102) has a core exhaust plane (86). The turbine section (108H,108L) has at least a first and a downstream second rotor blade row (80,82), with the core exhaust plane (86) located downstream of a center plane (88) of the second blade row (82).

Anmelder

Firmen

RTX Corporation
Raytheon Technologies Corporation
United Technologies Corporation

Land

🇺🇸 USA

Fachgebiete