Motor and motor controller thermal management features
A system includes a gas turbine engine configured to provide propulsion to an aircraft and a starter system configured to start the gas turbine engine. The starter system comprises a motor controller and a closed-loop cooling system configured to cool the motor controller during an emergency in-flight restart operation of the gas turbine engine. The closed-loop cooling system includes a cooling fluid reservoir containing cooling fluid. The cooling fluid is configured to receive thermal energy from the motor controller during the emergency in-flight restart operation of the gas turbine engine.
1. A system comprising:
a gas turbine engine configured to provide propulsion to an aircraft;
a starter system configured to start the gas turbine engine, wherein the starter system comprises a motor controller; and
a closed-loop cooling system configured to cool the motor controller during an emergency in-flight restart operation of the gas turbine engine, wherein the closed-loop cooling system includes a cooling fluid reservoir containing cooling fluid, wherein the cooling fluid is configured to receive thermal energy from the motor controller during the emergency in-flight restart operation of the gas turbine engine,
wherein the closed-loop cooling system does not include a heat exchanger configured to transfer thermal energy generated by the motor controller outside of the closed-loop cooling system.
2. The system of claim 1 , wherein:
the motor controller includes power switches, the power switches being configured to generate a power signal to control an electric machine configured to start the gas turbine engine,
the power switches generate heat while generating the power signal, and
the closed-loop cooling system is configured to cool the power switches during the emergency in-flight restart.
3. The system of claim 1 , wherein:
the closed-loop cooling system is sized to absorb a maximum amount of thermal energy, and
wherein the maximum amount of thermal energy is substantially equal to the maximum amount of thermal energy that can be generated during the emergency in-flight restart.
4. The system of claim 2 , wherein:
the closed-loop cooling system is configured to keep the power switches at or below a critical electronics temperature during the emergency in-flight restart, and
the critical electronics temperature is about 175 degrees Celsius.
5. The system of claim 3 , wherein a time period during which the emergency in-flight restart is conducted is from about 1 minute to about 15 minutes in duration.
6. The system of claim 1 , wherein the closed-loop cooling system comprises a liquid cooling fluid, and wherein the closed-loop cooling system includes a cooling fluid pump.
7. The system of claim 6 , wherein the liquid cooling fluid includes at least one of glycol or engine oil.
8. The system of claim 6 , wherein the cooling fluid pump is driven by a 28 - volt power supply.
9. The system of claim 1 , wherein at least a portion of a wall of the cooling fluid reservoir is configured to flex to change shape.
10. The system of claim 6 , further comprising a controller configured to activate the closed-loop cooling system from a non-operating condition to an operating condition during the emergency in-flight restart operation of the gas turbine engine.
11. The system of claim 10 , further comprising a temperature sensor, wherein the controller is configured to activate the closed-loop cooling system based at least partially on the temperature sensor sensing a critical electronics temperature.
12. The system of claim 10 , wherein the controller is configured to activate the closed-loop cooling system responsive to determining that the gas turbine engine is not in operation.
13. The system of claim 10 , wherein the motor controller comprises one or more cooling fins to remove thermal energy from the system through convective heat transfer.
14. The system of claim 13 , wherein at least one cooling fin of the one or more cooling fins comprises a phase change material on at least one surface of the fin, the phase change material configured to absorb thermal energy by changing phases from a solid to a liquid during the emergency in-flight restart.
15. The system of claim 2 , wherein the motor controller is at least partially surrounded by a jacket configured to contain the cooling fluid.
16. A method comprising:
starting a gas turbine engine configured to provide propulsion to an aircraft while the aircraft is in-flight by controlling a motor controller; and
cooling the motor controller with a closed-loop cooling system during an emergency in-flight restart operation of the gas turbine engine, wherein the closed-loop cooling system includes a cooling fluid reservoir containing cooling fluid, wherein the cooling fluid is configured to receive thermal energy from the motor controller during the emergency in-flight restart operation of the gas turbine engine, and wherein the closed-loop cooling system does not include a heat exchanger configured to transfer thermal energy generated by the motor controller outside of the closed-loop cooling system.
17. The method of claim 16 , further comprising;
generating, by power switches of the motor controller, a power signal to control an electric machine to start the gas turbine engine,
wherein the power switches increase in temperature while generating the power signal, and
wherein the closed-loop cooling system cools the power switches during the emergency in-flight restart.
18. The method of claim 16 , wherein cooling the motor controller during the emergency in-flight restart operation comprises cooling the motor controller for a time period that is from about 1 minute to about 15 minutes in duration.
19. The system of claim 1 , wherein the cooling fluid is configured to remain a liquid throughout a flight.