| 摘要 |
A turbomachine control system comprises an auxiliary hydraulic circuit 110 having at least one hydraulic actuator A1, A2 and servo valve S1, S2, the auxiliary circuit being suitable for being hydraulically connected parallel to a gas turbine / turbomachine main fuel circuit 114 or lubrication circuit (see figure 3), the auxiliary circuit comprising a dedicated / auxiliary pump 132 for powering the servo controlled actuator, the auxiliary pump being driven by an electric motor 150. Preferably the auxiliary circuit and secondary pump are part of an aircraft gas turbine engine fuel / lubricating oil system, with the electric motor being powered by the engine alternator. In this way, the geometry of the gas turbine / turbojet can be altered without affecting fuel / lubrication flow, during low rotational speeds of the turbojet.
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