PROGNOSTIC HEALTH MANAGEMENT APPROACHES FOR PROPULSION CONTROL SYSTEMS

• US 20140277991A1
• Filed: 03/11/2014
• Published: 09/18/2014
• Est. Priority Date: 03/15/2013
• Status: Active Grant

• Current Assignee: Rolls-Royce North American Technologies, Inc. (Rolls-Royce Holdings Plc)
• Original Assignee: Rolls-Royce North American Technologies, Inc. (Rolls-Royce Holdings Plc)
• Inventors: Skertic, Richard J., Myer, Joseph D.
• Granted Patent: US 9,790,864 B2
• Time in Patent Office: Days
• US Class Current: 701/100
• CPC Class Codes: F02C 9/00 Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants controlling air intakes F02C7/057; controlling turbines F01D; controlling compressors F04D27/00; controlling in general G05
• CPC Class Codes: G05B 23/0289 Reconfiguration to prevent failure, e.g. usually as a reaction to incipient failure detection

Abstract

A real-time gas turbine management system includes a controller system coupled to a gas turbine engine. The controller system is configured to control demand on a first and second component of a gas turbine engine. The controller system is configured to identify a set point reference of the first component, identify a set point reference of the second component, and identify a data set indicative of a level of deterioration of the gas turbine engine. The controller system is also configured to change the set point reference of the first component to extend a lifespan of the gas turbine engine and/or change the set point reference of the second component to extend the lifespan of the gas turbine engine.

Claims

1. A real-time gas turbine management system, comprising:

a controller system coupled to a gas turbine engine and configured to control demand on a first and second component of a gas turbine engine, the controller system is configured to;

identify a set point reference of the first component;

identify a set point reference of the second component;

identify a data set indicative of a level of deterioration of the gas turbine engine; and

change at least one of;

the set point reference of the first component to extend a lifespan of the gas turbine engine; and

the set point reference of the second component to extend the lifespan of the gas turbine engine.

2. The real-time gas turbine management system as claimed in claim 1, the controller system further configured to notify a user to change the set point reference of the second component.

3. The real-time gas turbine management system as claimed in claim 1, further comprising a prognostic data unit configured to determine the level of deterioration of the gas turbine engine.

4. The real-time gas turbine management system as claimed in claim 1, the control system further configured to:

receive a first set of sensed data indicative of a current operating characteristic of the first component; and

receive a second set of data indicative of a current operating characteristic of the second component.

5. The real-time gas turbine management system as claimed in claim 1, wherein the change of the set point reference of the first component is based on the first set of sensed data and the data set indicative of the level of deterioration of the gas turbine engine.

6. The real-time gas turbine management system as claimed in claim 1, wherein the change of the set point reference of the second component is based on a decrease in thrust from the gas turbine engine.

7. The real-time gas turbine management system as claimed in claim 1, wherein the set point reference of the first component is a fan speed set point reference and the set point reference of the second component is one of an engine power ratio set point reference and a turbo fan power ratio set point reference.

8. The real-time gas turbine management system as claimed in claim 1, the controller system is further configured to receive an engine control request, and wherein the change of the set point reference of the first component enables the gas turbine engine to meet the engine control request.

9. The real-time gas turbine management system as claimed in claim 8, wherein the engine control request is a request for additional thrust.

10. A system, comprising:

a real-time engine management system configured to;

receive an engine control request;

send a plurality of control demands to an engine, wherein each of the plurality of control demands each respectively control a plurality of components of the engine; and

receive a real-time operating characteristic of each of the plurality of components, wherein the real-time engine management system is programmed to;

identify an increased level of degradation of the system; and

based on the identification of the increased level of degradation, modify at least one control demand of the plurality of control demands so that the engine control request is met.

11. The system as claimed in claim 10, the real-time engine management system further programmed to determine a trim scheme to change the set point reference of the at least one control demand, wherein modification of the at least one control demand is based on the trim scheme.

12. The system as claimed in claim 11, wherein the plurality of control demands includes a fan speed control demand, a turbo fan power ratio control demand, and an engine power ratio control demand.

13. The system as claimed in claim 11, wherein modification of the at least one control demand modifies a fuel flow to the engine.

14. The system as claimed in claim 11, the real-time engine management system is further programmed to identify a difference between the at least one control demand and a sensed output of a first component of the plurality of components, wherein the first components corresponds with the at least one control demand, and wherein the modification of the at least one control demand is based on the difference.

15. A method of operating a turbine engine comprising:

receiving a demand for a turbine engine thrust;

identifying an active control mode of a system;

identifying an increased level of deterioration of the system; and

modifying a first set point reference of the active control mode to meet the demand for turbine engine thrust, wherein modifying the first set point reference is initiated by identifying the increased level of deterioration.

16. The method as claimed in claim 15, further comprising:

identifying an alternate control mode of the system; and

replacing the active control mode of the system with an alternate control mode of the system.

17. The method of claim 16, wherein the active control mode is a fan rotor speed control mode and the alternate control mode is an engine pressure ratio control mode.

18. The method of claim 16, wherein the active control mode is a turbo fan pressure ratio control mode.

19. The method of claim 17, further comprising determining a difference between a demand input for a component of the turbine engine and a sensed output of the component.

20. The method of claim 19, wherein modifying a first set point reference of the active control mode is based on the difference.