Patent ID: 8418964

Claim:
A fuel supply installation of an aircraft turbojet comprising: two volumetric pumps connected to combine their flow rates, the pumps including: a main pump driven mechanically by the turbojet and configured to supply substantially the required amount of fuel at a full gas rate of said turbojet; and a controlled auxiliary pump, configured to add additional fuel to said turbojet on ignition, so that the total fuel flow from both pumps is sufficient to provide the required amount of fuel for ignition; and a controller configured to selectively drive said auxiliary pump from startup to an ignition point of said turbojet, wherein said controller is configured to stop said auxiliary pump at an auxiliary pump stop drive speed which is faster than a drive speed of the ignition point of said turbojet, the auxiliary pump stop drive speed being a drive speed at which said auxiliary pump does not contribute to a flow rate of fuel at an intake of a regulator.