Methods and apparatus for trimming engine control systems

• US 6,459,963 B1
• Filed: 07/31/2000
• Issued: 10/01/2002
• Est. Priority Date: 07/31/2000
• Status: Expired due to Term

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: Bennett, George Washington, Wiseman, Matthew William, Adibhatla, Sridhar
• Primary Examiner(s): Cuchlinski, Jr., William A.
• Assistant Examiner(s): PIPALA, EDWARD J
• Application Number:
  US09/629,529
• Time in Patent Office: 792 Days
• Field of Search: 701/3, 701/14, 701/99, 701/100, 701/103, 701/104, 701/110, 701/115, 731/173, 602/04, 602/42, 60/390.3, 60/390.6
• US Class Current: 701/3
• CPC Class Codes: F02C 9/28 Regulating systems responsive to plant or ambient parameters, e.g. temperature, pressure, rotor speed F02C9/30 - F02C9/38, F02C9/44 take precedence

Abstract

A control system trims a gas turbine engine in real-time to provide a desired amount of thrust. The control system includes a controller coupled to the engine for receiving inputs from the engine regarding a status of the engine. The controller includes a processor and a non-volatile memory coupled to the processor. The processor is programmed to execute control logic. An engine power schedule representing values for a controlled variable is stored in the memory.

Claims

1. A method for controlling an aircraft engine using a control system, the control system including a processor coupled to the aircraft engine, said method comprising the steps of;

receiving a throttle command from the aircraft;

determining a reference value for a controlled variable from an engine power schedule;

generating a trim output based for the reference value based on current engine conditions;

adding the trim to the reference value to obtain a modified reference value;

comparing the modified reference value to a feedback value; and

determining a commanded fuel flow for a corresponding amount of thrust in response to the controlled variable.

2. A method in accordance with claim 1 wherein said step of generating a trim output further comprises the step of receiving engine sensor values used to generate the trim.

3. A method in accordance with claim 2 wherein said step receiving engine sensor values further comprises the steps of:

receiving an engine sensor value representing an exhaust gas temperature of the engine; and

receiving an engine sensor value representing a fan speed of the engine.

4. A method in accordance with claim 3 wherein said step of generating a trim output further comprises the step of using steady-state detection logic and at least one of a look-up table, a curve fit, and a physics model to generate the trim.

5. A method in accordance with claim 1 wherein said step of generating a trim output further comprises the steps of:

receiving a thrust demand value;

receiving a thrust estimate value; and

generating a trim in response to the thrust demand value and the thrust estimate value.

6. A control system for controlling an aircraft engine, said control system coupled to the aircraft engine for receiving a reference input from engine sensors coupled to the engine, said control system comprising a schedule memory storing an engine power schedule representing reference values for a controlled variable, said control system configured to generate a trim output for a reference value, said control system further configured to add the trim output to an engine power schedule reference value to produce a commanded fuel flow for a corresponding amount of thrust in response to the controlled variable and the engine sensor values.

7. A control system in accordance with claim 6 wherein said control system further configured to generate a trim output in response to the reference inputs received from the engine.

8. A control system in accordance with claim 6 wherein said control system further configured to use at least one of a lookup table, a curve-fit, and a physics model to generate the trim output.

9. A control system in accordance with claim 6 wherein said control system further comprises an estimator unit configured to receive health estimates of engine component health.

10. A control system in accordance with claim 9 wherein said control system further configured to use at least one of a regression matrix, a Kalman filter, and a neural network to receive health estimates of engine component health.

11. A control system in accordance with claim 10 wherein said control system further configured to receive exhaust gas temperature and fan speed values from the engine.

12. An aircraft engine trim system, said system coupled to the aircraft engine to receive reference inputs from the engine to determine a state of the aircraft engine, said system configured to generate a trim output in response to a thrust demand value and a thrust estimate value, said system comprising a schedule memory for storing an engine power schedule representing reference values for a controlled variable.

13. An aircraft engine trim system in accordance with claim 12 wherein said system further configured to determine a commanded fuel flow for a corresponding amount of thrust in response to the trim output using the reference inputs provided by the aircraft engine and a reference value provided by said schedule memory.

14. An aircraft engine trim system in accordance with claim 13 wherein said system further configured to use at least one of a lookup table, a curve-fit, and a physics model to generate the trim output.

15. An aircraft engine trim system in accordance with claim 12 wherein said system further configured to receive an engine throttle lever angle.

16. An aircraft engine trim system in accordance with claim 12 wherein control system further configured to receive health estimates of engine component health.

17. An aircraft engine trim system in accordance with claim 16 wherein said control system further configured to use at least one of a regression matrix, a Kalman filter, and a neural network to receive health estimates of engine component health.