Method of controlling a power generation system

• US 20060042258A1
• Filed: 08/27/2004
• Published: 03/02/2006
• Est. Priority Date: 08/27/2004
• Status: Active Grant

• Current Assignee: Siemens Energy Incorporated (Siemens AG)
• Original Assignee: Siemens Westinghouse Power Corporation
• Inventors: Schneider, Stefan, Singh, Jatinder, Gadde, Satish, Tadros, Fadi, Humphrey, Christopher
• Granted Patent: US 7,269,953 B2
• Time in Patent Office: Days
• US Class Current: 60/772
• CPC Class Codes: F01D 17/162 for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line F01D17/167 takes precedence
• CPC Class Codes: F02C 3/30 Adding water, steam or other fluids for influencing combustion, e.g. to obtain cleaner exhaust gases F02C7/141, F02C7/30, F01D21/00, F01K21/04, F23D11/10 take precedence
• CPC Class Codes: F02C 9/22 by adjusting turbine vanes
• CPC Class Codes: F02C 9/26 Control of fuel supply F02C9/48 takes precedence; fuel valves F02C7/232
• CPC Class Codes: F05D 2270/303 Temperature
• CPC Class Codes: Y02E 20/16 Combined cycle power plant [CCPP], or combined cycle gas turbine [CCGT]

Abstract

A method of controlling a gas turbine system (10) may include controlling an inlet guide vane position (98) to maintain a turbine (24) exhaust temperature at a corrected value that is a function of a compressor (12) inlet temperature and a turbine (24) normalized load. The method may include selecting the minimum value (138) of a part load tunable value, a part load maximum value and a fixed maximum value of a turbine (24) exhaust temperature for the corrected value. A corrected value setpoint may be determined (94) for the gas turbine system (10) operating at a part load condition where at least one of a fuel flow rate and the inlet guide vane position is controlled (98) so the corrected value does not exceed the corrected value setpoint. The corrected value may prevent a turbine (24) engine from exceeding its firing temperature during operation and ensure the engine operates within combustor dynamics and emissions limits.

Claims

1. A method of controlling a gas turbine system, the method comprising:

controlling an inlet guide vane position to maintain a turbine exhaust temperature at a corrected value that is a function of a compressor inlet temperature and a turbine normalized load.

2. The method of claim 1 further comprising:

selecting the corrected value to be a minimum value from the group consisting of a part load tunable corrected value, a part load maximum corrected value and a fixed maximum value of a turbine exhaust temperature.

3. The method of claim 1 further comprising:

controlling the turbine exhaust temperature at a baseload by controlling the fuel flow only with the inlet guide vane in a fully open position.

4. The method of claim 1 further comprising:

calculating the corrected value so that a turbine firing temperature is not exceeded when the turbine is operating.

5. The method of claim 1, the step of controlling further comprising:

determining a corrected value setpoint for the gas turbine system operating at a part load condition; and

controlling at least one of a fuel flow rate and the inlet guide vane position so the corrected value does not exceed the corrected value setpoint.

6. A method of controlling a gas turbine system comprising a compressor receiving air through inlet guide vanes, a combustor receiving compressed air from the combustor and fuel from a fuel system to produce hot combustion gas, and a turbine for expanding the hot combustion gas to extract work, the method comprising:

determining a corrected turbine exhaust temperature setpoint;

calculating a corrected turbine exhaust temperature; and

controlling at least one of an inlet guide vane position and a fuel flow rate to maintain the corrected turbine exhaust temperature within a limit of the corrected turbine exhaust temperature setpoint.

7. The method of claim 6 wherein the corrected turbine exhaust temperature is calculated as a function of a turbine exhaust temperature, a compressor inlet temperature and a turbine speed.

8. The method of claim 6 further comprising:

determining a turbine blade path temperature average;

activating an alarm if the turbine blade path temperature average exceeds a first limit;

unloading the turbine if the turbine blade path temperature average exceeds a second limit; and

tripping the turbine if the turbine blade path temperature average exceeds a third limit.

9. The method of claim 8 further comprising:

activating the alarm if the turbine blade path temperature average exceeds the first limit at a first combustor shell pressure;

unloading the turbine if the turbine blade path temperature average exceeds the second limit at a second combustor shell pressure; and

tripping the turbine if the turbine blade path temperature average exceeds the third limit at a third combustor shell pressure.

10. The method of claim 6 wherein the corrected turbine exhaust temperature is calculated as a function of a turbine exhaust temperature, a compressor inlet temperature and a turbine speed to prevent the turbine system from exceeding emission and combustor dynamic limits during operation.

11. The method of claim 6, further comprising:

calculating a maximum value for the corrected turbine exhaust temperature setpoint.

12. The method of claim 11 wherein the maximum value is calculated as a function of a turbine normalized load, a compressor inlet temperature and a turbine speed.

13. The method of claim 6 wherein the corrected turbine exhaust temperature setpoint is selected from the group consisting of a maximum turbine exhaust temperature, a part load corrected turbine exhaust temperature setpoint and a maximum corrected turbine exhaust temperature setpoint.

14. A closed loop inlet guide vane control apparatus for a gas turbine engine, the apparatus comprising:

an inlet guide vane positioner;

an inlet guide vane position sensor;

a combustor inlet temperature sensor;

a turbine outlet temperature sensor; and

a processor responsive to a signal from the turbine outlet temperature sensor and a signal from the combustor inlet temperature sensor to produce an output signal for controlling the inlet guide vane positioner.

15. The apparatus of claim 14, further comprising:

a fuel flow controller; and

wherein the processor is responsive to the signal from the turbine outlet temperature sensor and the signal from the combustor inlet temperature sensor to produce an output signal for controlling the fuel flow controller.

16. The apparatus of claim 14, further comprising:

a turbine speed sensor; and

wherein the processor is responsive to the signals from the turbine outlet temperature sensor and compressor inlet temperature sensor and to a signal from the turbine speed sensor to calculate a corrected turbine outlet temperature value.

17. A method of controlling a gas turbine engine, the method comprising:

calculating normalized power level as a function of a maximum power level achievable at a given ambient temperature;

controlling combustion in a combustor of the gas turbine engine to maintain an average blade path temperature below a predetermined maximum temperature;

controlling fuel delivery to the combustor in response to a power level demand; and

controlling inlet guide vane position to regulate a temperature responsive to a flame temperature in the combustor to a set point temperature compensated for a temperature responsive to inlet air temperature and for normalized power level.

18. The method of claim 17 further comprising controlling fuel delivery among a plurality of stages in the combustor in response to normalized power level.

19. The method of claim 17 further comprising further controlling fuel delivery to the combustor in the event that the control of inlet guide vane position is inadequate to regulate the temperature responsive to a flame temperature in the combustor to the set point temperature.

20. The method of claim 17 further comprising controlling combustion in the combustor to maintain the blade path temperature below a predetermined maximum temperature that varies as a function of combustor shell pressure.

21. The method of claim 17 further comprising setting the inlet guide vane to a full open position and controlling temperature responsive to a flame temperature in the combustor by controlling only fuel delivery once the gas turbine engine has achieved a 100% normalized power level.