Verzweigte Gasgeneratorabgasleitung an eine Freie Turbine

Details

Veröffentlichungs-Nr.

EP3284943

Aktenzeichen

EP17186611

Anmeldetag

17. August 2017

Veröffentlichung

14. Juli 2021

Erteilung

14. Juli 2021

Rechtsraum

EP

IPC

F02K3/062F02C3/10

Abstract

A gas turbine engine (15) for an aircraft (10) includes a core engine assembly (16A, 16B) including a compressor section (20A, 20B) communicating air to a combustor section (22) where the air is mixed with fuel and ignited to generate a high-energy gas flow that is expanded through a turbine section (24A, 24B). The turbine section (24A, 24B) is coupled to drive the compressor section (20A, 20B). A free turbine (26; 46A, 46B) is configured to be driven by gas flow from the core engine assembly (16A, 16B). A propulsor section (18) is aft of the core engine assembly (16A, 16B) and is driven by the free turbine (26; 46A, 46B). An exhaust duct (32) routes exhaust gases from the core engine assembly (16A, 16B) to the free turbine (26; 46A, 46B). The free turbine (26; 46A, 46B) is disposed aft of the propulsor section (18) and the exhaust duct (32) includes an outlet (25) aft of the propulsor section (18) communicating gas flow to drive the free turbine (26; 46A, 46B). An aircraft (10) is also disclosed.

Anmelder

Firmen

Raytheon Technologies Corporation
United Technologies Corporation

Land

🇺🇸 USA

Fachgebiete