Model-based optimal control for stall margin limit protection in an aircraft engine

1. A control system for a gas turbine engine, the gas turbine engine having a compressor section, the control system comprising:

a hybrid model predictive control (HMPC) module, the HMPC module receiving power goals and operability limits and determining a multi-variable control command for the gas turbine engine, the multi-variable control command determined using the power goals, the operability limits, actuator goals, sensor signals, and synthesis signals;

system sensors determining the sensor signals;

a non-linear engine model for estimating corrected speed signals and synthesis signals using the sensor signals, the synthesis signals including an estimated stall margin remaining;

a goal generation module for determining actuator goals for the HMPC module using the corrected speed signals; and

an actuator for controlling the gas turbine engine based on the multivariable control command.

2. The control system of claim 1 , wherein the HMPC module includes a state variable model of the gas turbine engine for determining the multi-variable control command.

3. The control system of claim 2 , wherein the HMPC module includes an optimization formulation, the optimization formulation receiving input from the state variable model, the power goals, and the operability limits to determine constrained optimization problem data.

4. The HMPC module of claim 3 , wherein the optimization formulation utilizes a dynamic model prediction horizon of one or more steps.

5. The control system of claim 3 , wherein the HMPC module includes an optimization solver, the optimization solver receiving input of the constrained optimization problem data from the optimization formulation to determine the multivariable control command.

6. The control system of claim 1 , wherein the operability limits include a stall margin remaining limit.

7. The control system of claim 1 , wherein the corrected speed signals include at least one of a corrected high pressure compressor speed and a corrected low pressure compressor speed.

8. The control system of claim 1 , wherein the sensor signals include sensed engine state variables, the sensed engine state variables including at least one of a speed associated with a component of the gas turbine engine, or a temperature of a component of a gas turbine engine.

9. The control system of claim 1 , wherein the synthesis signals include, at least, an engine thrust value associated with the gas turbine engine.

10. The control system of claim 1 wherein the power goals include at least one of a thrust goal, an engine spool speed goal, and a torque goal.

11. A method for controlling a gas turbine engine, the gas turbine engine including a compressor section, the method is performed by a control system, the method comprising:

determining sensor signals using system sensors;

estimating corrected speed signals and synthesis signals using the sensor signals, the synthesis signals including an estimated stall margin remaining;

determining actuator goals for a HMPC module using the corrected speed signals;

receiving power goals and operability limits by the HMPC module;

determining a multi-variable control command for the gas turbine engine using the HMPC module, the multi-variable control command determined using the power goals, the operability limits, actuator goals, sensor signals, and synthesis signals; and

controlling the gas turbine engine based on the multivariable control command using an actuator.

12. The method of claim 11 , wherein determining the multi-variable control command further includes using an optimization formulation of the HMPC module, the optimization formulation receiving input from the state variable model, the power goals, and the operability limits to determine constrained optimization problem data.

13. The method of claim 12 , wherein determining the multi-variable control command further includes using an optimization solver of the HMPC module, the optimization solver receiving input of the constrained optimization problem data from the optimization formulation.

14. A gas turbine engine comprising:

a compressor section;

a combustor section downstream of the compressor section;

a turbine section downstream of the combustor section; and

a control system comprising:

a hybrid model predictive control (HMPC) module, the HMPC module receiving power goals and operability limits and determining a multi-variable control command for the gas turbine engine, the multi-variable control command determined using the power goals, the operability limits, actuator goals, sensor signals, and synthesis signals;

system sensors determining the sensor signals;

a non-linear engine model for estimating corrected speed signals and synthesis signals using the sensor signals, the synthesis signals including an estimated stall margin remaining;

a goal generation module for determining actuator goals for the HMPC module using the corrected speed signals; and

actuators for controlling the gas turbine engine based on the multivariable control command.

15. The gas turbine engine of claim 14 , wherein the compressor section includes a high pressure compressor and a low pressure compressor.

16. The gas turbine engine of claim 14 , wherein the multi-variable control command includes a fuel flow rate to control fuel flow of the combustor section.

17. The gas turbine engine of claim 14 , wherein the multi-variable control command includes instructions for the actuator to position a vane of the compressor section.

18. The gas turbine engine of claim 17 , wherein the vane is at least one of a low pressure compressor stator vane or a high pressure compressor stator vane.

19. The gas turbine engine of claim 14 , wherein the multi-variable control command includes instructions for positioning a bleed of the compressor section.

20. The gas turbine engine of claim 14 , further comprising an exit nozzle, wherein the multi-variable control command includes instructions for positioning the exit nozzle.