Compressor operability control for hybrid electric propulsion
A hybrid electric propulsion system includes a gas turbine engine having a low speed spool and a high speed spool. The low speed spool includes a low pressure compressor and turbine, and the high speed spool includes a high pressure compressor and turbine. The hybrid electric propulsion system includes an electric generator configured to extract power from the low speed spool, an electric motor configured to augment rotational power of the high speed spool, and a controller. The controller is operable to determine a target operating condition of the low pressure compressor to achieve a compressor stability margin in the gas turbine engine, determine a current operating condition of the low pressure compressor, and control a power transfer between the electric generator of the low speed spool and the electric motor of the high speed spool to adjust the current operating condition based on the target operating condition.
1. A hybrid electric propulsion system comprising:
a gas turbine engine comprising a low speed spool and a high speed spool, the low speed spool comprising a low pressure compressor and a low pressure turbine, and the high speed spool comprising a high pressure compressor and a high pressure turbine;
an electric generator coupled to the low speed spool and configured to extract power from the low speed spool;
an electric motor coupled to the high speed spool and configured to augment rotational power of the high speed spool; and
a controller configured to:
determine a target operating condition of the low pressure compressor to achieve a compressor stability margin in the gas turbine engine;
determine a current operating condition of the low pressure compressor; and
control a power transfer from the electric generator of the low speed spool to the electric motor of the high speed spool to adjust the current operating condition based on the target operating condition that reduces a pressure ratio of the low compressor.
2. The hybrid electric propulsion system of claim 1 , wherein the target operating condition of the low pressure compressor is determined by the controller with respect to one or more engine properties used to estimate stability of the low pressure compressor.
3. The hybrid electric propulsion system of claim 2 , wherein the one or more engine properties comprise one or more of: a vane angle, a compressor corrected speed, a compressor pressure ratio, a compressor flow corrected at compressor inlet properties, and a compressor flow corrected at compressor exit properties.
4. The hybrid electric propulsion system of claim 2 , wherein the target operating condition is based on a target pressure ratio of the low pressure compressor associated with a low pressure compressor corrected air flow, the current operating condition comprises a current pressure ratio of the low pressure compressor and a current corrected flow, and the low pressure compressor corrected air flow and the current pressure ratio are adjusted based on the target pressure ratio.
5. The hybrid electric propulsion system of claim 4 , wherein the controller is further configured to adjust the target pressure ratio based on a rate of change in speed of the low pressure compressor.
6. The hybrid electric propulsion system of claim 1 , wherein an exhaust gas temperature of the gas turbine engine is reduced based on transferring power from the electric generator of the low speed spool to the electric motor of the high speed spool while maintaining a substantially constant thrust.
7. The hybrid electric propulsion system of claim 1 , wherein the controller is further configured to transfer power from the electric generator to an energy storage system.
8. The hybrid electric propulsion system of claim 7 , wherein the controller is further configured to transfer power from the energy storage system to the electric motor.
9. The hybrid electric propulsion system of claim 1 , wherein the controller is further configured to transfer power from the electric generator to the electric motor of the high speed spool absent a change in output of a low pressure compressor vane actuator of the gas turbine engine.
10. The hybrid electric propulsion system of claim 1 , wherein the target operating condition comprises a target pressure ratio associated with a combination of low pressure compressor corrected air flow and vane angle.
11. A method for controlling a hybrid electric propulsion system, the method comprising:
determining, by a controller, a target operating condition of a low pressure compressor to achieve a compressor stability margin in a gas turbine engine comprising a low speed spool and a high speed spool, the low speed spool comprising the low pressure compressor and a low pressure turbine, and the high speed spool comprising a high pressure compressor and a high pressure turbine;
determining, by the controller a current operating condition of the low pressure compressor; and
controlling a power transfer from an electric generator coupled to the low speed spool to an electric motor coupled to the high speed spool to adjust the current operating condition of the low pressure compressor based on the target operating condition that reduces a pressure ratio of the low compressor.
12. The method of claim 11 , wherein the target operating condition of the low pressure compressor is determined by the controller with respect to one or more engine properties used to estimate stability of the low pressure compressor.
13. The method of claim 12 , wherein the one or more engine properties comprise one or more of: a vane angle, a compressor corrected speed, a compressor pressure ratio, a compressor flow corrected at compressor inlet properties, and a compressor flow corrected at compressor exit properties.
14. The method of claim 12 , wherein the target operating condition is based on a target pressure ratio of the low pressure compressor associated with a low pressure compressor corrected air flow, the current operating condition comprises a current pressure ratio of the low pressure compressor and a current corrected flow, and the low pressure compressor corrected air flow and the current pressure ratio are adjusted based on the target pressure ratio.
15. The method of claim 14 , wherein the controller is further configured to adjust the target pressure ratio based on a rate of change in speed of the low pressure compressor.
16. The method of claim 11 , wherein an exhaust gas temperature of the gas turbine engine is reduced based on transferring power from the electric generator of the low speed spool to the electric motor of the high speed spool while maintaining a substantially constant thrust.
17. The method of claim 11 , further comprising:
transferring power from the electric generator to an energy storage system.
18. The method of claim 17 , further comprising:
transferring power from the energy storage system to the electric motor.
19. The method of claim 11 , further comprising:
transferring power from the electric generator to the electric motor of the high speed spool absent a change in output of a low pressure compressor vane actuator of the gas turbine engine.
20. The method of claim 11 , wherein the target operating condition comprises a target pressure ratio associated with a combination of low pressure compressor corrected air flow and vane angle.