Flugzeugtriebwerksauslassabschnitt mit Strömungsumlenker

Details

Veröffentlichungs-Nr.

EP4722524

Anmeldetag

26. September 2025

Veröffentlichung

8. April 2026

Rechtsraum

EP

IPC

F02K1/00

Abstract

An aircraft powerplant (20) includes a core (28) of a gas turbine engine (24) and an exhaust section (26). The core includes a core flowpath (40), a compressor section (36), a combustor section (37) and a turbine section (38). The core flowpath extends longitudinally through the compressor section, the combustor section and the turbine section. The exhaust section includes an exhaust flowpath (60) and a flow diverter (66). The flow diverter includes a diverter panel (70) configured to pivot between a first position and a second position. The flow diverter is configured to fluidly couple the diffuser section (72) to the first nozzle section (76) and fluidly decouple the diffuser section from the second nozzle section (82) when the diverter panel is in the first position. The flow diverter is configured to fluidly couple the diffuser section to the second nozzle section and fluidly decouple the diffuser section from the first nozzle section when the diverter panel is in the second position.

Anmelder

Firma

PRATT & WHITNEY CANADA CORP.

Land

🇨🇦 Kanada