Verfahren und System zur Wärmeregelung in einem Flugzeug

Details

Veröffentlichungs-Nr.

EP2423106

Aktenzeichen

EP11178268

Anmeldetag

22. August 2011

Veröffentlichung

17. Juli 2019

Erteilung

17. Juli 2019

Rechtsraum

EP

IPC

B64D11/00B64D13/00B64D15/04// B64D13/06B64D33/02

Abstract

A thermal management system (TMS) (200) includes an engine heat exchanger (304) configured to transfer waste heat from a propulsive engine (20) to a pumped heat transfer fluid, an engine exhaust heat exchanger (206) coupled in flow communication with the engine heat exchanger, the engine exhaust heat exchanger configured to transfer heat from an exhaust of the propulsive engine to the pumped heat transfer fluid, a bypass valve (208) coupled in parallel with the engine exhaust heat exchanger, the bypass valve selectable to modulate a flow of the pumped heat transfer fluid through the engine exhaust heat exchanger, and a plurality of accessory heat exchangers for each of a plurality of heat loads of a vehicle coupled in flow communication with at least one of the engine heat exchanger and the engine exhaust heat exchanger, each the plurality of accessory heat exchangers flow controllable using a modulating valve.

Anmelder

Firma

GE Aviation Systems LLC

Land

🇺🇸 USA

Fachgebiete