Wärmemanagement einer Gasturbinenmotorwelle

Details

Veröffentlichungs-Nr.

EP3575574

Aktenzeichen

EP19174731

Anmeldetag

15. Mai 2019

Veröffentlichung

28. April 2021

Erteilung

28. April 2021

Rechtsraum

EP

IPC

F02C6/06F02C7/18F02C7/32F01D25/12

Abstract

A gas turbine engine (20; 100; 200) includes a fan rotor (42), a compressor section (24), a combustor section (26), and a turbine section (28). The turbine section (28) is positioned downstream of the combustor section (26). A fan drive turbine (106) in the turbine section (28), and a shaft (138) connects the fan drive turbine (106) to the fan rotor (42). An inlet duct (114; 214) is connected to a cooling air source and connected to a cooling compressor (118; 252) downstream of the fan drive turbine (106). The cooling compressor (118; 252) is connected to an air source, and connected to a turning duct (124; 224) for passing compressed air in an upstream direction through the shaft (138). A method is also disclosed.

Anmelder

Firmen

Raytheon Technologies Corporation
United Technologies Corporation

Land

🇺🇸 USA

Fachgebiete