Flugzeugantriebssystem mit Turboverdichtereinheit

Details

Veröffentlichungs-Nr.

EP4741634

Anmeldetag

10. November 2025

Veröffentlichung

13. Mai 2026

Rechtsraum

EP

IPC

F01D9/02, F01D9/04, F01D9/06

Abstract

An aircraft propulsion system (20) includes a turbocompressor unit (40), an engine exhaust assembly (32), and a tube assembly (118). The turbocompressor unit (40) includes a compressor (44), a turbine (42), a turbocompressor rotational assembly (46), and a static structure (48). The static structure (48) forms a first cavity (72) and a second cavity (84). The engine exhaust assembly (32) includes an annular scroll (38) disposed between the first cavity (72) and the second cavity (84). The annular scroll (38) includes a scroll body (86) forming a flow channel (90), and a plurality of hollow stator vanes (94). The plurality of hollow stator vanes (94) is disposed within the flow channel (90). The tube assembly (118) includes a tubular body (120). The tubular body (120) extends through one of the plurality of hollow stator vanes (94) between and to the first cavity (72) and the second cavity (84). The tubular body (120) forms an internal passage (112) extending from the first axial tube end (130) to the second axial tube end (132). The internal passage (112) connects the first cavity (72) in fluid communication with the second cavity (84).

Anmelder

Firma

PRATT & WHITNEY CANADA CORP.

Land

🇨🇦 Kanada