Gasturbinenmotor mit Umgekehrter Strömung und Elektrischer Maschine

Details

Veröffentlichungs-Nr.

EP4417796

Aktenzeichen

EP24151475

Anmeldetag

11. Januar 2024

Veröffentlichung

4. März 2026

Erteilung

4. März 2026

Rechtsraum

EP

IPC

F02C6/20F02C7/18F02C3/10F01D15/10F02C3/14

Abstract

An aircraft engine (10) assembly comprising: a gas turbine engine (10) having a high pressure compressor (22), a high pressure turbine (28), a high pressure shaft (34) coupling the high pressure compressor (22) with the high pressure turbine (28), a low pressure turbine, and a low pressure shaft (36) coupled to the low pressure turbine, the high pressure turbine (28) located forward of the high pressure compressor (22), and the low pressure turbine located on a forward end of the gas turbine engine (10); an intake channel (54) of the gas turbine engine (10) configured to receive an incoming flow of air and form an intake flow of air, the intake channel (54) configured to turn the received incoming flow of air from an incoming flow direction to a first axial direction of the gas turbine engine (10), the incoming flow direction reverse of the first axial direction; and an electric machine (74, 74a, 74b) coupled with the low pressure shaft (36) and located on a side of the high pressure compressor (22) opposite of the high pressure turbine (28) and proximate the intake channel (54), the electric machine (74, 74a, 74b) in heat exchange communication with the intake flow of air such that the electric machine (74, 74a, 74b) transfers heat to the incoming flow of air within the intake channel (54) when the electric machine (74, 74a, 74b) is operated.

Anmelder

Firmen

General Electric Company
GE Aerospace Poland sp. z o.o.
General Electric Company Polska sp. z o.o.

Land

🇺🇸 USA

Fachgebiete