System and method for coordinated control of a power system
An integrated gas turbine engine, electrical power subsystem and thermal management subsystem for aerospace application includes a first motor/generator coupled to a low pressure (LP) shaft of the gas turbine engine, a second motor/generator coupled to a high pressure (HP) shaft of the gas turbine engine, and a system controller coupled to each of the gas turbine engine, a first motor generator and a second motor/generator, wherein the controller receives engine thrust demand and electrical power demand and is programmed to determine total system power demand and the amount of power sharing between the first motor/generator and the second motor/generator to meet thrust and electrical power demand.
1. An integrated gas turbine engine, electrical power subsystem and thermal management subsystem for aerospace application, comprising:
a first motor/generator coupled to a low pressure (LP) shaft of the gas turbine engine;
a second motor/generator coupled to a high pressure (HP) shaft of the gas turbine engine;
a system controller coupled to each of the gas turbine engine, the first motor/generator, and the second motor/generator, wherein the system controller is programmed to determine an amount of power sharing between the first motor/generator and the second motor/generator to meet a power demand and control a gas generator portion of the gas turbine engine using a total system power demand as a control variable;
a first energy storage unit coupled to the first motor/generator,
a second energy storage unit coupled to the second motor/generator,
wherein the system controller is further programmed to meet the power demand, which includes an amount of engine thrust, by storing energy to and drawing the energy from at least one of the first energy storage unit and the second energy storage unit, in order to provide the amount of engine thrust as needed;
wherein the power demand includes a total electrical load provided to an aircraft, and the controller is further programmed to control operation of at least one of the first motor/generator and the second motor/generator to meet the total electrical load; and
wherein during a motoring mode when the first motor/generator operates as a motor, the system controller decelerates the aircraft to a reduced thrust by a fan of the aircraft by decreasing an amount of energy being provided by the first motor/generator; and
wherein during a generating mode when the first motor/generator operates as a generator, and when the LP shaft provides power to the fan of the aircraft and to the first motor/generator, the system controller decelerates the aircraft to the reduced thrust by the fan by:
i. when keeping an amount of combustion power constant, increasing the amount of energy provided to the first motor/generator; and
ii. when reducing the amount of combustion power, first by increasing the amount of energy provided to the first motor/generator and then second by reducing the amount of energy provided to the first motor generator.
2. The subsystem of claim 1 , wherein the power demand includes the amount of engine thrust and the controller is further programmed to control operation of the first motor/generator to provide the power demand via application of one of the motoring mode, a braking, a motoring release, and a braking release of the LP shaft to achieve the power demand.
3. The subsystem of claim 1 , wherein the controller is further programmed to augment the amount of engine thrust produced in the gas turbine engine by affecting the amount of power sharing between the first motor/generator and the second motor/generator.
4. The subsystem of claim 1 , wherein the power demand includes the amount of engine thrust and the controller is further programmed to control an amount of energy storage to and from the at least one of the first energy storage unit and the second energy storage unit in conjunction with controlling operation of one of the first motor/generator and the second motor/generator.
5. The subsystem of claim 1 , wherein the power demand includes the total electrical load and the controller is further programmed to control an amount of energy storage to and from at least one of the first energy storage unit and the second energy storage unit in conjunction with controlling operation of the first motor/generator and the second motor/generator.
6. The subsystem of claim 1 , wherein the amount of engine thrust is further reduced by extracting electrical power from the LP shaft and providing the electrical power to the first energy storage unit via the first motor/generator.
7. The subsystem of claim 1 , wherein a fuel flow is decreased in the gas turbine engine to meet a reduced total system power demand due to the reduced thrust, and as a torque applied to the LP shaft decreases, electrical power extracted from the first motor/generator correspondingly decreases.
8. The subsystem of claim 1 , wherein a platform electrical load includes overall electrical requirements for the aircraft, and wherein for a constant platform electrical load the deceleration of the aircraft to the reduced thrust further includes reducing an amount of electrical energy storage supplied by one of the first and second energy storage units while correspondingly decreasing an amount of torque to the LP shaft.
9. A method of controlling an integrated gas turbine engine, electrical power subsystem and thermal management subsystem for aerospace application as an integrated multivariable system, comprising:
receiving engine thrust demand, which includes an amount of engine thrust, and electrical power demand from an aircraft;
determining a total system power demand;
determining an amount of power sharing between a first motor/generator and a second motor/generator to meet the total system power demand; wherein:
the first motor/generator is coupled to a low pressure (LP) shaft of the gas turbine engine and to a first energy storage unit; and
the second motor/generator is coupled to a high pressure (HP) shaft of the gas turbine engine and to a second energy storage unit;
controlling a gas generator portion of the gas turbine engine using the total system power demand as a control variable;
storing energy to provide the engine thrust to, and drawing the energy from, at least one of the first energy storage unit and second energy storage unit to provide the engine thrust;
controlling operation of at least one of the first motor generator and the second motor/generator to meet the total system power demand that includes the electrical power demand provided to the aircraft;
wherein during a motoring mode when the first motor/generator operates as a motor, decelerating the aircraft to a reduced thrust by a fan of the aircraft by decreasing an amount of energy being provided by the first motor/generator; and
wherein during a generating mode when the first motor/generator operates as a generator, and when the LP shaft provides power to the fan of the aircraft and to the first motor/generator, decelerating the aircraft to the reduced thrust by the fan by:
i. when keeping an amount of combustion power constant, increasing the amount of energy provided to the first motor/generator; and
ii. when reducing the amount of combustion power, first by increasing the amount of energy provided to the first motor/generator and then second by reducing the amount of energy provided to the first motor generator.
10. The method of claim 9 , further comprising controlling operation of the first motor/generator to provide the engine thrust demand via application of one of the motoring mode, a braking, a motoring release, and a braking release of the LP shaft to achieve the engine thrust demand.
11. The method of claim 9 , further comprising augmenting the amount of engine thrust produced in the gas turbine engine by affecting the amount of power sharing between the first motor/generator and the second motor/generator.
12. The method of claim 9 , wherein the total system power demand includes the amount of engine thrust, further comprising controlling an amount of energy storage to and from the at least one of the first energy storage unit and second energy storage unit in conjunction with controlling operation of one of the first motor/generator and the second motor/generator.
13. The method of claim 9 , further comprising controlling an amount of energy storage to and from at least one of the first energy storage unit and the second energy storage unit in conjunction with controlling operation of the first motor/generator and the second motor/generator.
14. The method of claim 9 , wherein the total system power demand includes the amount of engine thrust and an amount of power to the LP shaft.
15. The method of claim 9 , further comprising reducing the engine thrust by extracting electrical power from the LP shaft and providing the electrical power to the first energy storage unit via the first motor/generator.
16. The method of claim 8 , further comprising decreasing a fuel flow in the gas turbine engine to meet a reduced total system power demand due to the reduced thrust, and as a torque applied to the LP shaft decreases, electrical power extracted from the first motor/generator correspondingly decreases.
17. An integrated gas turbine engine, electrical power subsystem and thermal management subsystem, comprising:
a first motor/generator coupled to a low pressure (LP) shaft of the gas turbine engine;
a second motor/generator coupled to a high pressure (HP) shaft of the gas turbine engine;
a system controller coupled to each of the gas turbine engine, the first motor/generator, and the second motor/generator, and programmed to determine an amount of power sharing between the first motor/generator and the second motor/generator to meet a power demand, and further programmed to meet the power demand, which includes an amount of engine thrust, by storing energy to and drawing the energy from at least one of a first energy storage unit and a second energy storage unit, in order to provide the amount of engine thrust as needed;
wherein the power demand includes a total electrical load provided to an aircraft in a motoring mode and a generating mode, and the controller is further programmed to control operation of at least one of the first motor/generator and the second motor/generator to meet the total electrical load;
wherein during a motoring mode when the first motor/generator operates as a motor, the system controller decelerates the aircraft to a reduced thrust by a fan of the aircraft by decreasing an amount of energy being provided by the first motor/generator; and
wherein during a generating mode when the first motor/generator operates as a generator, and when the LP shaft provides power to the fan of the aircraft and to the first motor/generator, the system controller decelerates the aircraft to the reduced thrust by the fan by:
i. when keeping an amount of combustion power constant, increasing the amount of energy provided to the first motor/generator; and
ii. when reducing the amount of combustion power, first by increasing the amount of energy provided to the first motor/generator and then second by reducing the amount of energy provided to the first motor generator.
18. The subsystem of claim 17 , wherein the power demand includes the amount of engine thrust and the controller is further programmed to control operation of the first motor/generator to provide the power demand via application of one of the motoring mode, a braking, a motoring release, and a braking release of the LP shaft to achieve the power demand.
19. The subsystem of claim 17 , wherein the controller is further programmed to augment the amount of engine thrust produced in the gas turbine engine by affecting the power sharing between the first motor/generator and the second motor/generator.
20. The subsystem of claim 17 , wherein the power demand includes the amount of engine thrust and the controller is further programmed to control an amount of energy storage to and from the at least one of the first energy storage unit and the second energy storage unit in conjunction with controlling operation of one of the first motor/generator and the second motor/generator.