GAS TURBINE HYDRAULIC LUBRICATION SYSTEM

System for an aircraft, the system comprising: a turbine engine (2) with a hydraulic lubrication circuit (30); and a fuel cell (28) with a hydraulic circuit (40) for setting and maintaining the operating temperature of the fuel cell (28); wherein the hydraulic lubrication circuit (30) and the hydrau...

Ausführliche Beschreibung

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Bibliographische Detailangaben
Hauptverfasser:	CORNET, Albert, RAIMARCKERS, Nicolas
Format:	Patent
Sprache:	eng ; fre ; ger
Schlagworte:	AIR INTAKES FOR JET-PROPULSION PLANTS BASIC ELECTRIC ELEMENTS BLASTING COMBUSTION ENGINES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS ELECTRICITY ENGINE PLANTS IN GENERAL GAS-TURBINE PLANTS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS LIGHTING MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES PROCESSES OR MEANS, e.g. BATTERIES, FOR THE DIRECT CONVERSIONOF CHEMICAL INTO ELECTRICAL ENERGY STEAM ENGINES WEAPONS
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Beschreibung
Zusammenfassung:	System for an aircraft, the system comprising: a turbine engine (2) with a hydraulic lubrication circuit (30); and a fuel cell (28) with a hydraulic circuit (40) for setting and maintaining the operating temperature of the fuel cell (28); wherein the hydraulic lubrication circuit (30) and the hydraulic circuit (40) form a single and common oil circuit and the oil circuit comprises a pump (50) with a heating element integrated in the pump for heating the oil.The pump may be an electric pump with an electric motor, wherein the electric motor comprises a coil fed with DC current forming a heating element for heating the oil.The pump may comprise a body and the heating element may be an electric resistor embedded into the body of the pump and in direct contact with the oil.