Zapfluftsystem und Verfahren zum Betrieb davon

Details

Veröffentlichungs-Nr.

EP3208446

Aktenzeichen

EP17156775

Anmeldetag

17. Februar 2017

Veröffentlichung

9. September 2020

Erteilung

9. September 2020

Rechtsraum

EP

IPC

F02C7/18F02C9/18F02C6/08F01D25/02

Abstract

A bleed air system (65) for an aircraft includes a turbocompressor (62) including a turbine portion (76) coupled to drive a compressor portion (74). The compressor portion (74) includes a compressor inlet (100) and a compressor air discharge (102). The turbine portion (76) includes a turbine inlet (96) and a turbine discharge (98). A passage (66) delivers air to the compressor inlet (100) from one or more locations of an engine (20). A passage (68) delivers air to the turbine inlet (96) from at least one or more locations of the engine (20). A passage receives air from the compressor discharge (102) selectively delivered to one or more locations of the engine (20). An outlet passage (64) receives air from the turbine discharge (98) communicating airflow to an aircraft system (70, 72). A controller (90) directs inlet and discharge airflow of the compressor portion (74) and the turbine portion (76) to control operation of the turbocompressor (62). A gas turbine engine (20) and a method are also disclosed.

Anmelder

Firmen

Raytheon Technologies Corporation
United Technologies Corporation

Land

🇺🇸 USA

Fachgebiete