Aircraft engine with cooling for an electric starting device

F - Mech Eng,Light,Heat,Weapons – 02 – C

Patent

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Details

F02C 7/14 (2006.01) F02C 7/236 (2006.01) F02C 7/275 (2006.01)

Patent

CA 2752526

The invention relates to an aircraft engine, including a fuel-pumping device comprising a high-pressure fuel pump (26) having an inlet connected to a low-pressure fuel pipe (28) and an outlet connected to a main high-pressure fuel supply circuit, an electric device (40) for starting the engine and a cooling device for the electric starting device connected to the pumping device for cooling the fuel by circulation. The cooling device (54, 56, 58) is supplied with fuel by a pump (50) having an inlet connected to the pumping device upstream from the high-pressure pump (26) and which is driven by an electric motor (52) independently from the high-pressure pump (26).

Le moteur aéronautique comprend un dispositif de pompage de carburant comportant une pompe de carburant haute pression (26) ayant une entrée reliée à une conduite (28) de carburant basse pression et une sortie reliée à un circuit principal d'alimentation en carburant haute pression, un dispositif électrique (40) de démarrage du moteur et un dispositif de refroidissement du dispositif électrique de démarrage relié au dispositif de pompage pour assurer le refroidissement par circulation de carburant. Le dispositif de refroidissement (54, 56, 58) est alimenté en carburant par une pompe (50) qui a une entrée reliée au dispositif de pompage, en amont de la pompe haute pression (26) et qui est entraînée par un moteur électrique (52) indépendamment de la pompe haute pression (26).

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