Turbinenstützgehäuse mit Axialen Speichen und Halteelementen

Details

Veröffentlichungs-Nr.

EP4722498

Anmeldetag

26. September 2025

Veröffentlichung

8. April 2026

Rechtsraum

EP

IPC

F01D9/02, F01D25/16, F01D25/24

Abstract

An aircraft engine (10), has: a turbine (15); a scroll case (20) having an inlet (22) connected to a source of combustion gases (19) and an outlet (23) connected to the turbine (15), and a conduit (21) extending from the inlet (22) to the outlet (23); a bearing housing (30) including a support flange; an exhaust case (15B) downstream of the turbine (15); and a turbine support case (40) secured to the bearing housing (30) and to the exhaust case (15B), the turbine support case (40) having spokes (44) extending along a direction having an axial component, the spokes (44) extending through the scroll case (20) and radially supported by the bearing housing (30), a spoke having a distal end (44B) secured to the support flange via: one or more fasteners (47), and a retaining member (48) at the distal end (44B), the retaining member (48) defining an abutment face (48A) facing an axial direction and circumferentially overlapping the support flange, a portion of the support flange located axially between the distal end (44B) and the abutment face (48A).

Anmelder

Firma

PRATT & WHITNEY CANADA CORP.

Land

🇨🇦 Kanada