Method and system for modulated turbine cooling as a function of engine health

1. A modulated turbine cooling (MTC) control system comprising a processor in communication with a memory, wherein said processor is programmed to:

determine a first cooling flow requirement of an engine component for each of a plurality of operating conditions comprising one or more flight conditions, wherein the flight conditions includes at least a takeoff condition, a climb condition, a cruise condition, and a descent condition;

channel the first cooling flow requirement to the engine component during each respective operating condition of the plurality of operating conditions;

assess a health of the engine component;

determine a second cooling flow requirement based on the first cooling flow requirement, the assessed health of the engine component, and the flight condition; and

supply the second cooling flow requirement to the engine component during each subsequent respective operating condition of the plurality of operating conditions.

2. The MTC control system of claim 1 , wherein said processor is further programmed to assess the health of the engine component in real-time during operation of the engine component.

3. The MTC control system of claim 1 , wherein said processor is further programmed to modulate a position of a valve configured to supply the second cooling flow requirement.

4. The MTC control system of claim 1 , wherein said processor is further programmed to assess the health of the engine component using at least one of one or more sensors, one or more virtual sensors, and one or more models of the engine component.

5. The MTC control system of claim 4 , wherein said processor is further programmed to estimate the health of the engine component using a health model and a parameter estimation algorithm.

6. A method of modulating cooling flow to an engine component based on a health of the engine component, said method performed by a processor in communication with a memory, the processor configured to execute steps of the method comprising:

determining a first cooling flow requirement of the engine component for each of a plurality of operating conditions, the plurality of operating conditions comprising one or more flight conditions, wherein the flight conditions includes at least a takeoff condition, a climb condition, a cruise condition, and a descent condition;

channeling the first cooling flow requirement to the engine component during each respective operating condition of the plurality of operating conditions;

assessing a health of the engine component;

determining a second cooling flow requirement based on the first cooling flow requirement, the assessed health of the engine component, and the flight condition; and

supplying the second cooling flow requirement to the engine component during each subsequent respective operating condition of the plurality of operating conditions.

7. The method of claim 6 , wherein assessing the health of the engine component comprises assessing the health of the engine component in real-time during operation of the engine component.

8. The method of claim 6 , wherein the engine component is one of a plurality of gas turbine engine components, and wherein supplying the second cooling flow requirement to the engine component during each subsequent respective operating condition of the plurality of operating conditions comprises at least one of:

reducing a specific fuel consumption (SFC) of the gas turbine engine during operation when supplying the second cooling flow requirement to the engine component compared to channeling the first cooling flow to the engine component, and

increasing a time-on-wing of the gas turbine engine when supplying the second cooling flow requirement to the engine component compared to channeling the first cooling flow to the engine component.

9. The method of claim 6 , wherein supplying the second cooling flow requirement to the engine component during each subsequent respective operating condition of the plurality of operating conditions comprises modulating a position of a valve configured to supply the second cooling flow requirement.

10. The method of claim 6 , wherein assessing the health of the engine component comprises assessing the health of the engine component using at least one of one or more sensors, one or more virtual sensors, and one or more models of the engine component.

11. The method of claim 10 , wherein assessing the health of the engine component comprises estimating the health of the engine component using a health model and a parameter estimation algorithm.

12. A turbofan engine comprising:

a core engine including a multistage compressor;

a fan powered by a turbine driven by gas generated in said core engine;

a fan bypass duct at least partially surrounding said core engine and said fan; and

a modulated turbine cooling (MTC) control system in communication with at least one engine component of said turbofan engine, said MTC control system comprising a processor in communication with a memory, wherein said processor is programmed to:

determine a first cooling flow requirement for a health of the engine component for each of a plurality of operating conditions comprising one or more flight conditions, wherein the flight conditions includes at least a takeoff condition, a climb condition, a cruise condition, and a descent condition;

channel the first cooling flow requirement to the engine component during each respective operating condition of the plurality of operating conditions;

estimate the health of the engine component using a health model and a parameter estimation algorithm;

assess the health of the engine component;

determine modify the determined a second cooling flow requirement based on the first cooling flow requirement, the assessed health of the engine component, and the flight condition; and

supply the second cooling flow requirement to the engine component during each subsequent respective operating condition of the plurality of operating conditions.

13. The turbofan engine of claim 12 , wherein said processor is further programmed to assess the health of the engine component in real-time during operation of the engine component.

14. The turbofan engine of claim 12 , wherein said processor is further programmed to modulate a position of a valve configured to supply the second cooling flow requirement.

15. The turbofan engine of claim 12 , wherein said processor is further programmed to assess the health of the engine component using at least one of one or more sensors, one or more virtual sensors, and one or more models of the engine component.

16. The turbofan engine of claim 12 , wherein said engine component comprises the turbine, and wherein said first cooling flow requirement is channeled from said compressor to said turbine.

17. The turbofan engine of claim 12 , wherein determining the second cooling flow requirement based on the first cooling flow requirement, the assessed health of the engine component and the flight condition includes decreasing cooling flow to said turbine at the cruise condition relative to one or more of the takeoff condition or the climb condition.

18. The turbofan engine of claim 12 , wherein said processor is further programmed to increase a time-on-wing of the turbofan engine, or reduce a specific fuel consumption (SFC) of the turbofan engine, or both, during operation when supplying the second cooling flow requirement to the engine component compared to channeling the first cooling flow requirement to the engine component.