Gekühlte Kühlluft für Schaufelluftabdichtung durch die Aussenkammer

Details

Veröffentlichungs-Nr.

EP3382156

Aktenzeichen

EP18165234

Anmeldetag

29. März 2018

Veröffentlichung

30. Dezember 2020

Erteilung

30. Dezember 2020

Rechtsraum

EP

IPC

F01D11/24F01D9/06

Abstract

A gas turbine engine (20) includes a compressor section (24), a combustor (56), and a turbine section (28). The combustor (56) has a radially outer surface that defines a diffuser chamber (112) radially outwardly of the combustor (56). The turbine section (28) has a high pressure turbine first stage blade (118) that has an outer tip, and a blade outer air seal (126) positioned radially outwardly of the outer tip. A tap (102) for tapping air has been compressed by the compressor (56) and is passed through a heat exchanger (104). The air downstream of the heat exchanger (104) passes through at least one pipe (120) and into a manifold (122) radially outward of the blade outer air seal (126), and then passes across the blade outer air seal (126) to cool the blade outer air seal (126).

Anmelder

Firmen

Raytheon Technologies Corporation
United Technologies Corporation

Land

🇺🇸 USA

Fachgebiete