Abgasgehäuse für Flugzeugtriebwerk

Details

Veröffentlichungs-Nr.

EP4764169

Anmeldetag

19. Dezember 2025

Veröffentlichung

24. Juni 2026

Rechtsraum

EP

IPC

F01D25/24, F01D25/30

Abstract

An exhaust system (15) for an aircraft engine of an aircraft having a direction of travel, 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) communicating with the annular inlet conduit (33) and extending generally radially outward relative to the annular inlet conduit (33); and an exhaust case (18D) enclosing the TED (30), the exhaust case (18D) extending from a forward end (18F) to a rearward end (18R) relative to the direction of travel, the exhaust case (18D) having openings (18E), each of the outlet conduits (34, 35) received through a respective one of the openings (18E); and reinforcing members (40) secured to the exhaust cases between the forward end (18F) and the rearward end (18R), the reinforcing members (40) being located opposite circumferential sides of the openings (18E) and locally increasing a thickness of the exhaust case.

Anmelder

Firma

Pratt & Whitney Canada Corp.

Land

🇨🇦 Kanada

Fachgebiete