Fuel supply apparatus for aircraft engine
Two systems of a first pump unit and a third pump unit that supply fuel of a fuselage fuel tank, and a second pump unit and a fourth pump unit that supply fuel of fuel tanks in both right and left wings are provided corresponding to a left-wing engine and a right-wing engine, respectively. A supply source of the fuel to be supplied to the left-wing engine or the right-wing engine is switched by switching of the pump unit to be turned on.
1. A fuel supply apparatus for an aircraft, the apparatus comprising:
a first pump unit configured to supply fuel from a fuselage fuel tank of the aircraft to a first engine provided in a left wing of the aircraft;
a second pump unit configured to supply fuel from fuel tanks in both wings of the aircraft to the first engine;
a third pump unit configured to supply the fuel from the fuselage fuel tank to a second engine provided in a right wing of the aircraft;
a fourth pump unit configured to supply the fuel from the fuel tanks in the both wings to the second engine; and
a computer configured to selectively switch the pump units that supply the fuel to each engine, respectively, wherein
each pump unit has a booster and a measuring unit;
the booster includes:
a centrifugal pump and a gear pump configured to boost and supply fuel to a corresponding engine of the first engine and the second engine, and
an electric motor configured to rotationally drives the centrifugal pump and the gear pump; and
the measuring unit is configured to measure a supply amount of the fuel to the corresponding engine.
2. The fuel supply apparatus according to claim 1 , further comprising:
a first ejector pump including:
a suction port connected to the fuselage fuel tank,
a supply port connected to an outlet of the centrifugal pump in the third pump unit, and
a discharge port connected to a first fuel supply path from the fuel tanks in the both wings to the second pump unit,
the first ejector pump being configured to supply fuel from the fuselage fuel tank to the first fuel supply path, when the fuel is supplied from the second pump unit to the first engine, and the fuel is supplied from the third pump unit to the second engine; and
a second ejector pump including:
a suction port connected to the fuselage fuel tank,
a supply port connected to an outlet of the centrifugal pump in the first pump unit, and
a discharge port connected to a second fuel supply path from the fuel tanks in the both wings to the fourth pump unit,
the second ejector pump being configured to supply fuel from the fuselage fuel tank to the second fuel supply path from the fuel tanks in the both wings to the fourth pump unit, when the fuel is supplied from the fourth pump unit to the second engine, and the fuel is supplied from the first pump unit to the first engine.
3. The fuel supply apparatus according to claim 1 , wherein the measuring unit includes:
a fixed orifice,
a pressurizing valve provided in parallel to the fixed orifice, and
a differential pressure gauge which measures a differential pressure between an upstream side and a downstream side of a parallel flow passage of the fixed orifice and the pressurizing valve.