Electric windmill pump for gearbox durability
A gas turbine engine installed on an aircraft includes a fan rotor, a turbine rotor, a gearbox, an auxiliary pump, and an electric motor. The gearbox couples the fan rotor to the turbine rotor, the turbine rotor being adapted to drive the fan rotor via the gearbox. The auxiliary pump is configured to circulate lubricating fluid in an auxiliary lubrication system and supplies the gearbox. The electric motor is configured to receive electricity when the aircraft is parked an adapted to drive the auxiliary pump such that the auxiliary pump circulates lubricating fluid while the aircraft is parked.
1. A gas turbine engine comprising:
a fan rotor;
a low pressure turbine rotor;
a high pressure turbine rotor in an axial flow arrangement with the low pressure turbine rotor;
a fan drive gearbox coupled to the fan rotor and the low pressure turbine rotor, wherein the low pressure turbine rotor is adapted to drive the fan rotor via the fan drive gearbox, the fan drive gearbox comprising:
a bearing;
a main lubrication system configured to supply one or more sumps;
an auxiliary pump configured to circulate lubricating fluid in an auxiliary lubrication system, wherein the auxiliary lubrication system supplies the fan drive gearbox;
a supply line fluidly connecting an output of the auxiliary pump to a lubricating surface of the bearing;
an electric motor adapted to drive the auxiliary pump;
a controller; and
a sensor adapted to detect windmilling rotation of the fan rotor, wherein the sensor transmits a signal to the controller when the windmilling fan rotor rotates, and wherein so long as the sensor detects rotation of the windmilling fan rotor at a speed that is less than a threshold speed of sixty revolutions per minute, the controller is configured to supply power to the electric motor intermittently, thereby driving the auxiliary pump intermittently.
2. The gas turbine engine of claim 1 , and further comprising:
a compartment enclosing the fan drive gearbox and configured to receive lubrication fluid from the main lubrication system and the auxiliary lubrication system; and
an auxiliary reservoir disposed within the gas turbine engine such that, in operation, lubrication fluid collects therein, wherein the auxiliary reservoir communicates with the compartment, and wherein the auxiliary pump is disposed within the auxiliary reservoir.
3. The gas turbine engine of claim 2 , and further comprising:
an inner case;
an outer case disposed radially outward from the inner case with respect to a centerline of the gas turbine engine; and
a strut extending from the inner case to the outer case, wherein walls of the strut form at least a portion of the auxiliary reservoir.
4. The gas turbine engine of claim 2 , and further comprising:
an engine panel moveably connected to the gas turbine engine such that the engine panel has a closed position configured to enclose at least a portion of the gas turbine engine and an open position configured to provide access to an interior of the gas turbine engine;
wherein the electric motor is positioned outside the auxiliary reservoir within the interior of the gas turbine engine and is accessible and removable when the engine panel is in the open position and while the auxiliary reservoir remains attached to the gas turbine engine.
5. The gas turbine engine of claim 4 , wherein the engine panel is a cowling door pivotally attached to the gas turbine engine.
6. The gas turbine engine of claim 2 , and further comprising:
a return line fluidly connecting the auxiliary reservoir to the main lubrication system;
a shuttle valve disposed along the return line that is actuated to an open state when a pressure of the main lubrication system exceeds a threshold value and actuated to a closed state when the pressure is less than the threshold value, wherein the closed position of the shuttle valve isolates the compartment from the main lubrication system such that lubrication fluid is retained within the auxiliary reservoir.
7. The gas turbine engine of claim 1 , wherein the electric motor receives power from a ground auxiliary power unit.
8. The gas turbine engine of claim 1 , wherein the electric motor receives power from a cable connecting the electric motor to a ground power grid.
9. The gas turbine engine of claim 1 , wherein the electric motor receives power from a rechargeable battery mounted to the gas turbine engine.
10. The gas turbine engine of claim 9 , and further comprising:
a generator configured to produce electric power, wherein the generator is coupled to the fan rotor such that rotation of the fan rotor drives rotation of the generator;
wherein the rechargeable battery receives electric power from the generator when the fan rotor rotates.
11. The gas turbine engine of claim 1 , wherein the gas turbine engine is mounted to an aircraft, and wherein the electric motor receives power from batteries mounted within the aircraft.
12. A turbofan engine installed on an aircraft, the turbofan engine comprising:
a fan rotor;
a low pressure turbine rotor;
a high pressure turbine rotor in an axial flow arrangement with the low pressure turbine rotor;
a fan drive gearbox coupled to the fan rotor and the low pressure turbine rotor, wherein the low pressure turbine rotor is adapted to drive the fan rotor via the fan drive gearbox, the fan drive gearbox comprising:
a bearing;
a main lubrication system configured to supply one or more sumps;
an auxiliary pump configured to circulate lubricating fluid in an auxiliary lubrication system supplying the fan drive gearbox;
an electric motor configured to receive electricity when the aircraft is parked and adapted to drive the auxiliary pump;
a controller; and
a sensor adapted to detect windmilling rotation of the fan rotor, wherein the sensor transmits a signal to the controller when the windmilling fan rotor rotates at a speed less than a predetermined threshold speed,
wherein so long as the sensor detects windmilling rotation of the fan rotor less than the predetermined threshold speed of sixty revolutions per minute, the controller is configured to supply power to the electric motor intermittently, thereby driving the auxiliary pump intermittently to circulate a lubricating fluid within the auxiliary lubrication system while the aircraft is parked.
13. The turbofan engine of claim 12 , and further comprising:
a compartment enclosing the gearbox and configured to receive lubrication fluid from the main lubrication system and the auxiliary lubrication system; and
an auxiliary reservoir disposed relative to the compartment such that when the turbofan engine is installed on the aircraft that is parked lubrication fluid from the compartment collects within the auxiliary reservoir, wherein the auxiliary pump is disposed within the auxiliary reservoir such that an inlet of the auxiliary pump is immersed by lubrication fluid collected therein.
14. The turbofan engine of claim 12 , wherein the electric motor is positioned outside the auxiliary reservoir, and wherein the electric motor is a line replaceable unit.