Turbinenstützgehäuse mit Axialen Speichen und Hitzeschilden

Details

Veröffentlichungs-Nr.

EP4726178

Anmeldetag

10. Oktober 2025

Veröffentlichung

15. April 2026

Rechtsraum

EP

IPC

F01D25/24

Abstract

An aircraft engine (10), has: a turbine (15) including a turbine rotor (15C) rotatable about a central axis (A); a scroll case (20) having an inlet (22) connected to a source of combustion gases (19) and an outlet (23) fluidly connected to the turbine (15), and a conduit (21) extending around the central axis (A) from the inlet (22) to the outlet (23); a bearing housing (30); a turbine support case (40) secured to the bearing housing (30), the scroll case (20) disposed axially between the turbine support case (40) and 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); and heat shields (60) distributed around the central axis (A) in circumferential alignment with the spokes (44) and extending axially through the scroll case (20) for thermally shielding the spokes (44), a heat shield of the heat shields (60) disposed around a spoke of the spokes (44), the heat shield (60) defining an air gap (G1) surrounding the spoke (44) inside the scroll case (20).

Anmelder

Firma

PRATT & WHITNEY CANADA CORP.

Land

🇨🇦 Kanada