Abgasgehäuse für Flugzeugtriebwerk

Details

Veröffentlichungs-Nr.

EP4764167

Anmeldetag

19. Dezember 2025

Veröffentlichung

24. Juni 2026

Rechtsraum

EP

IPC

F01D25/24, F01D25/30

Abstract

An exhaust system (15) for an aircraft engine, has: a turbine exhaust duct, TED, (30) having an annular inlet conduit (33) extending around a central axis (17) for directing combustion gases generally in an axial direction, and outlet conduits (34; 35) fluidly communicating with the annular inlet conduit (33) and extending generally radially outward relative to the annular inlet conduit (33); and an exhaust case (40) surrounding the TED (30), the exhaust case (40) having: a frustoconical section (42) extending from a fore end (42A) at an intersection with a remainder of the exhaust case (40) to an aft end (42B) securable to a turbine case (18C) of the aircraft engine, the frustoconical section (42) converging towards the central axis (17) from the fore end (42A) to the aft end (42B); and a connecting flange (42C) at the aft end (42B), the connecting flange (42C) protruding inwardly towards the central axis (17).

Anmelder

Firma

Pratt & Whitney Canada Corp.

Land

🇨🇦 Kanada

Fachgebiete