Turbinenabgaskanal mit Sondenschnittstelle

Details

Veröffentlichungs-Nr.

EP4782664

Anmeldetag

26. Januar 2026

Veröffentlichung

29. Juli 2026

Rechtsraum

EP

Abstract

An exhaust system for an aircraft engine has: a turbine exhaust duct, TED, (30) having an annular inlet conduit extending around a central axis for directing combustion gases generally in an axial direction, and outlet conduits branching off from the annular inlet conduit; and an exhaust case (18D) surrounding the TED, the exhaust case being frustoconical and having outlet openings (18E) each communicating with a respective one of the outlet conduits, a probe opening extending through the exhaust case and bounded by a periphery, and a probe interface (40) mounted to the periphery of the probe opening, the probe interface including an interfacing plate secured to the periphery of the probe opening and defining an aperture sized to receive a probe therethrough, the aperture located radially inwardly of the probe opening.

Anmelder

Firma

Pratt & Whitney Canada Corp.

Land

🇨🇦 Kanada