Gekühlte Luftzufuhr für einen Turbinenmotor

Details

Veröffentlichungs-Nr.

EP4807159

Anmeldetag

11. März 2026

Veröffentlichung

16. September 2026

Rechtsraum

EP

IPC

F02C6/08, F02C7/224, F02C9/26

Abstract

An aircraft has a gas turbine engine. A first fuel flowpath (410) passes from a fuel source (202) to a combustor (70). An air-air heat exchanger has a heat donor leg along a bleed flowpath and a heat recipient leg along a bypass flowpath. An air-fuel heat exchanger (86) has a heat donor leg (120) along the bleed flowpath downstream of the air-air heat exchanger. A second fuel flowpath (420) passes from the fuel source (202) through the air-fuel heat exchanger (86) and includes a heat recipient leg (122) of the air-fuel heat exchanger (86) and at least partially non-overlapping the first fuel flowpath (410). One or more third fuel flowpaths (430) pass from the fuel source (202) through fuel-driven actuators (230). The second fuel flow path (420) and the one or more third fuel flowpaths (430) return to the fuel source (202) or the first fuel flowpath (410).

Anmelder

Firma

RTX Corporation

Land

🇺🇸 USA

Fachgebiete