Lufteinlass für eine Motoranordnung eines Flugzeugantriebssystems

Details

Veröffentlichungs-Nr.

EP4528089

Aktenzeichen

EP24202672

Anmeldetag

25. September 2024

Veröffentlichung

2. Juli 2025

Rechtsraum

EP

IPC

F02C7/04B64D33/02F02C7/36

Abstract

An engine assembly (20) for an aircraft propulsion system (10) includes a gas turbine engine (22), a gearbox (24), and a first drive shaft (30). The gas turbine engine (22) includes an engine output shaft (64), an air intake (34), and a compressor (44). The air intake (34) includes an air intake body (86) forming an air inlet (88), an air outlet (90), and an air plenum (92) extending between and connecting the air inlet (88) and the air outlet (90). The air plenum (92) extends circumferentially about the engine output shaft (64) between and to a first circumferential end (104) of the air intake (34) and a second circumferential end (106) of the air intake (34). The first circumferential end (104) and the second circumferential end (106) form a circumferential gap (108). The compressor (44) is connected in fluid communication with the air intake (34). The gearbox (24) includes a gear assembly (68) operably connected to the engine output shaft (64). The first drive shaft (30) is operably connected to the gear assembly (68). The first drive shaft (30) extends through the circumferential gap.

Anmelder

Firma

PRATT & WHITNEY CANADA CORP.

Land

🇨🇦 Kanada

Fachgebiete