METHOD AND SYSTEMS FOR CONTROLLING ENGINE THRUST USING VARIABLE TRIM

• US 20100275575A1
• Filed: 04/30/2009
• Published: 11/04/2010
• Est. Priority Date: 04/30/2009
• Status: Active Grant

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: Brown, Harold
• Granted Patent: US 8,381,510 B2
• Time in Patent Office: Days
• US Class Current: 60/204
• 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: 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
• CPC Class Codes: F05D 2270/051 Thrust
• CPC Class Codes: F05D 2270/708 with comparison tables

Abstract

A method and systems for controlling a thrust output of a gas turbine engine are provided. The system includes a first sensor for measuring a first engine operating parameter, a second sensor for measuring a first engine condition parameter, and a processor programmed to determine an expected value of the first engine condition parameter and determine a first variance value using a difference between the expected value of the first engine condition parameter and the measured first engine condition parameter. The processor is further programmed to determine a trim value using the first variance value and a first engine operating parameter demand and to determine a modified operating parameter demand based on the nominal operating parameter demand and the determined trim value. The system also includes a controller coupled to the processor for controlling engine thrust based on the modified demand of the first engine operating parameter.

Claims

1. A thrust control system for use in controlling the thrust output of a gas turbine engine, said thrust control system comprising:

a first sensor for measuring a first engine operating parameter;

a second sensor for measuring a first engine condition parameter;

a processor programmed to;

determine an expected value of the first engine condition parameter using the measured first engine operating parameter value;

determine a first variance value, using a difference between the expected value of the first engine condition parameter and the measured first engine condition parameter;

determine a trim value for controlling the first engine operating parameter using the first variance value and a first engine operating parameter demand;

determine a modified operating parameter demand based on the nominal operating parameter demand and the determined trim value; and

a controller coupled to said processor for receiving the determined modified operating parameter demand value from the processor, said controller configured to control engine thrust based on the modified demand of the first engine operating parameter.

2. A system in accordance with claim 1 wherein the first engine operating parameter is at least one of a fan speed, a core engine pressure ratio, and a liner engine pressure ratio.

3. A system in accordance with claim 1 wherein the first engine condition parameter is at least one of a low pressure turbine discharge temperature, a high pressure rotor inlet temperature, a low pressure turbine rotor inlet temperature, and an exhaust gas temperature.

4. A system in accordance with claim 1 wherein said processor is further programmed to use a lookup table that provides the expected value of the first engine condition parameter using at least one of altitude, Mach number, inlet temperature, and power setting.

5. A system in accordance with claim 4 wherein said look-up table comprises data generated by at least one of empirical testing the same type of gas turbine engine as the gas turbine engine coupled to said system and a computer model based on the same type of gas turbine engine coupled to said system.

6. A system in accordance with claim 4 wherein said look-up table further comprises a table of expected engine temperature values as a function of the fan speed, and at least one of an altitude, a Mach number, an engine inlet temperature, and a throttle setting.

7. A system in accordance with claim 1 wherein said controller is configured to control the engine thrust using at least one of a core engine pressure ratio (CEPR), a fan speed value, and a liner engine pressure ratio.

8. A method of automatically controlling a thrust output of a gas turbine engine, said method comprising:

determining an expected value of the second engine parameter wherein the expected value is a value expected for an engine operating at current operating conditions;

determining a difference between the expected value and the second engine parameter;

determining an engine trim value using the difference;

modifying a current demand of the first engine parameter using the engine trim value; and

controlling the thrust output of the gas turbine engine using the modified current demand.

9. A method in accordance with claim 8, wherein measuring a second engine parameter comprises measuring at least one of a low pressure turbine discharge temperature, a high pressure rotor inlet temperature, a low pressure turbine rotor inlet temperature, and an exhaust gas temperature.

10. A method in accordance with claim 8, wherein measuring a first engine parameter comprises measuring at least one of an engine fan speed, an engine pressure ratio, and a liner engine pressure ratio.

11. A method in accordance with claim 8, wherein determining the expected value comprises determining the expected value of the second engine parameter using an engine performance database.

12. A method in accordance with claim 11, further comprising accessing an onboard engine performance database comprising data generated by testing an engine of the same type as the gas turbine engine.

13. A method in accordance with claim 8, wherein determining the engine trim value further comprises:

classifying a level of engine deterioration based on the difference;

determining a change in the operating parameter demand based on the engine deterioration classification.

14. A method in accordance with claim 8, wherein controlling the thrust output further comprises changing one of a fan speed and a core engine pressure ratio by an amount equivalent to the trim value.

15. A gas turbine engine system comprising:

a fan; and

a thrust control system comprising;

a first sensor operatively coupled to the gas turbine engine, said first sensor configured to measure a first engine parameter;

a second sensor operatively coupled to the engine, said second sensor configured to measure a second engine parameter;

a processor communicatively coupled to the first sensor and the second sensor, said processor programmed to determine an expected value of the second engine parameter using the first engine parameter, said processor further programmed to;

generate a variance value using a difference between the expected value and the second engine parameter;

generate a trim value using the variance value; and

modify a current demand of the first engine parameter by the trim value; and

a controller communicatively coupled to the processor and the gas turbine engine, said controller configured to control engine thrust using the modified current demand and the first operating parameter.

16. A system in accordance with claim 15 wherein the first engine parameter comprises at least one of a fan speed and a core engine pressure ratio (CEPR).

17. A system in accordance with claim 15 wherein the second engine parameter comprises at least one of a low pressure turbine discharge temperature, a high pressure rotor inlet temperature, a low pressure turbine rotor inlet temperature, and an exhaust gas temperature.

18. A system in accordance with claim 15 wherein the controller changes the amount of engine thrust by changing at least one of a core engine pressure ratio (CEPR) and a fan speed.

19. A system in accordance with claim 15 further comprising a memory device comprising a look-up table of expected temperature values versus fan speeds and at least one of altitudes, Mach numbers, and inlet temperatures.

20. A system in accordance with claim 19 wherein said look-up table comprises data generated by at least one of computer modeling an engine of the same type as the gas turbine engine and testing an engine of the same type as the gas turbine engine.