Turbinenstützgehäuse Gestützt durch Anschlagrippen

Details

Veröffentlichungs-Nr.

EP4726180

Anmeldetag

10. Oktober 2025

Veröffentlichung

15. April 2026

Rechtsraum

EP

IPC

F01D25/24

Abstract

An aircraft engine (10), has: a turbine (15); a scroll case (20) connected to a source of combustion gases (19) and to the turbine (15), and a conduit (21) extending around a central axis (A); a bearing housing (30) including a support flange (41); a turbine support case (40) secured to the bearing housing (30), the turbine support case (40) having spokes (44) extending through the scroll case (20) and radially supported by the bearing housing (30), a spoke of the spokes (44) having a distal end (44B) secured to the support flange (41) via one or more fasteners (47); and ribs (41A,60) secured to the support flange (41) and distributed around the central axis (A), a rib (60) of the ribs (41A,60) circumferentially and axially overlapping the distal end (44B) of the spoke (44), the rib (60) having a rib face (61) in radially opposed facing relationship to a spoke face (44D) of the spoke (44), a projection of the rib face (61) in a circumferential direction relative to the central axis (A) intersecting the spoke face (44D).

Anmelder

Firma

PRATT & WHITNEY CANADA CORP.

Land

🇨🇦 Kanada

Fachgebiete