An aircraft hydraulic thermal management system utilizes fuel to cool hydraulic fluid by means of a heat exchanger. A hydraulic pump includes a case drain flow of hydraulic fluid at a first temperature to drive a hydraulic motor; the hydraulic motor circulates hydraulic fluid to a reservoir at a second temperature. The heat exchanger is positioned remotely of the fuel tank, and has first and second channels positioned in thermal communication to transfer heat from the hydraulic fluid to the fuel. The hydraulic motor is mechanically coupled to the fuel pump; the hydraulic motor, driven by case drain flow through the first channel, thus operates the fuel pump to move fuel through the second channel. The thermal management system is configured to assure that a) the hydraulic pump circulates hydraulic fluid to the reservoir at the second temperature, and b) the second temperature is always lower than the first temperature.
Aircraft hydraulic thermal management system
2018-03-20
Patent
Elektronische Ressource
Englisch
IPC: | B23P Sonstige Metallbearbeitung , OTHER WORKING OF METAL / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / F01P Kühlung von Kraft- und Arbeitsmaschinen oder Kraftmaschinen allgemein , COOLING OF MACHINES OR ENGINES IN GENERAL / F15B SYSTEMS ACTING BY MEANS OF FLUIDS IN GENERAL , Druckmittelbetriebene Systeme allgemein |
Thermal management system, aircraft and aircraft thermal management method
Europäisches Patentamt | 2023
|Europäisches Patentamt | 2022
|