Turbinenabgaskanal für Flugzeugtriebwerk

Details

Veröffentlichungs-Nr.

EP4764170

Anmeldetag

19. Dezember 2025

Veröffentlichung

24. Juni 2026

Rechtsraum

EP

IPC

F01D25/24, F01D25/30

Abstract

A turbine exhaust duct, TED, (30) for an aircraft engine, has: an annular inlet conduit (33) extending around a central axis (17) for directing combustion gases generally in an axial direction; outlet conduits (34; 35) communicating with the annular inlet conduit (33) and extending generally radially outward relative to the annular inlet conduit (33), the outlet conduits (34; 35) extending from inlet ends (34A; 35A) at intersections with the annular inlet conduit (33) to outlet ends (34B; 35B), an outlet conduit of the outlet conduits (34; 35) having: a forward section (34F; 35F) facing an axially forward direction and a rearward section (35R; 35R) opposite the forward section (34F; 35F), the forward section (34F; 35F) and the rearward section (35R; 35R) conjointly defining an outlet end of the outlet ends (34B; 35B); and a reinforcement plate (40) secured to the forward section (34F; 35F), the reinforcement plate (40) having a thickness (T1) greater than a baseline thickness (T0) of the outlet conduit outside the reinforcement plate (40).

Anmelder

Firma

Pratt & Whitney Canada Corp.

Land

🇨🇦 Kanada

Fachgebiete