Microprocessor-based control system for gas turbine electric powerplant

• US 6,789,000 B1
• Filed: 04/16/2002
• Issued: 09/07/2004
• Est. Priority Date: 04/16/2002
• Status: Expired due to Fees

• Current Assignee: Altek Power Corp.
• Original Assignee: Altek Power Corp.
• Inventors: Munson, Bill C. Jr.
• Primary Examiner(s): Picard, Leo
• Assistant Examiner(s): KASENGE, CHARLES R
• Application Number:
  US10/123,715
• Time in Patent Office: 875 Days
• Field of Search: 700/287, 700/289, 700/290, 477/30, 477/31, 477/121, 602/39, 602/261, 602/37, 361/51, 290/40.R, 290/40.A
• US Class Current: 700/287
• CPC Class Codes: F01D 19/00 Starting of machines or engines; Regulating, controlling, or safety means in connection therewith warming-up before starting F01D25/10; turning or inching gear F01D25/34
• CPC Class Codes: F01D 21/00 Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
• 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 2270/54 by electronic means, e.g. electronic tubes, transistors or IC's within an electronic circuit

Abstract

A microprocessor-based control system for a gas turbine electrical powerplant the microprocessor-based control system controls the startup, operation, and shutdown of the gas turbine electric powerplant. The microprocessor-based control system of the present invention dispenses with the need to utilize relays, timers, or other control hardware. Rather, the microprocessor-based control system employs software that replaces the control hardware, and directly reads the inputs, calculates the control actions, and writes the outputs. The microprocessor-based control system is also in electrical communication with an overspeed control system, provided to ensure that a runaway condition of the gas turbine engine does not occur should the gas turbine engine become disconnected from the speed reducer (gearbox) or generator. Sensors are used to monitor multiple operating conditions of the powerplant. The microprocessor-based control system communicates with the sensors, and activates the overspeed control system if an overspeed condition is detected.

Claims

1. A control system for a gas turbine electric powerplant having a high rotational speed gas turbine engine, comprising:

a microprocessor;

sensors for monitoring various conditions of said gas turbine electric powerplant;

a fuel flow control means for controlling a supply of fuel to said gas turbine engine;

an air removal means for permitting air to be rapidly vented from a combustion section of said gas turbine engine in response to a signal from said microprocessor;

an air directing means for controlling the direction of air flowing into said gas turbine engine;

software in electrical communication with said microprocessor, said sensors, said fuel flow control means, said air removal means, and said air directing means; and

a means of inputting setpoint data to said software;

wherein, said software reads said setpoint data, determines appropriate control actions, and directly activates one or more appropriate control devices, thereby allowing said control system to automatically operate said gas turbine electric powerplant; and

wherein said fuel flow control means, said air removal means, and said air directing means are used substantially simultaneously to automatically control an overspeed condition of said gas turbine engine, even when said gas turbine electric powerplant is operating in an unattended state.

2. The control system of claim 1, wherein said sensors are provided to monitor conditions selected from the group consisting of turbine speed, exhaust gas temperature, inlet air temperature, oil temperature, generator winding temperature, generator bearing temperature, gearbox bearing temperature, oil pressure, generator output, and inlet guide vane position.

3. The control system of claim 1, wherein said means of inputting setpoint data is a keyboard.

4. The control system of claim 1, wherein said means of inputting setpoint data is a touch screen.

5. The control system of claim 1, further comprising a fuel control valve in communication with said software, said fuel control valve having an integrated microprocessor that compares demand signals from said software with actual fuel flow, and makes adjustments to said valve accordingly.

6. The control system of claim 5, wherein said fuel control valve controls a supply of liquid fuel.

7. The control system of claim 5, wherein said fuel control valve controls a supply of gaseous fuel.

8. The control system of claim 1, further comprising an actuator in communication with said software, said actuator adapted, in response to a signal from said software, to alter the angle of a set of inlet guide vanes within a gas turbine engine of said gas turbine electric powerplant.

9. The control system of claim 1, further comprising a compression relief solenoid valve in communication with said software, said solenoid valve adapted, in response to a signal from said software, to allow the transfer of air from a combustion section of a gas turbine engine of said gas turbine electric powerplant.

10. The control system of claim 1, further comprising means for viewing gas turbine electric powerplant conditions.

11. The control system of claim 1, wherein said software is adapted to provide predictive modeling.

12. A microprocessor-based control system for a gas turbine electric powerplant having an aeroderivative gas turbine engine, comprising:

a plurality of sensors for monitoring various gas turbine electric powerplant conditions;

a compression relief system comprising a means for rapidly removing air from a combustion portion of said gas turbine engine during operation thereof, in response to a signal from said microprocessor;

an air directing system for altering the angle at which incoming air impinges a set of compressor blades located within said gas turbine engine;

software in communication with said microprocessor, said sensors, said compression relief system, and said air directing system;

a fuel control valve for controlling the supply of fuel to said turbine engine, said fuel control valve in communication with said software and having an integrated microprocessor that compares demand signals from said software with actual fuel flow, and makes adjustments to said valve accordingly; and

a means of inputting setpoint data to said software;

wherein, said software reads said setpoint data, determines appropriate control actions, and directly activates one or more appropriate control devices, thereby allowing said control system to automatically operate said gas turbine electric powerplant; and

wherein said compression relief system, said air directing system, and said fuel control valve are manipulated substantially simultaneously by said control system in response to detection of an overspeed condition of said gas turbine engine;

whereby said overspeed condition is automatically controlled even when said gas turbine electric powerplant is operating in an unattended state.

13. The control system of claim 12, wherein said sensors are provided to monitor conditions selected from the group consisting of turbine speed, exhaust gas temperature, inlet air temperature, oil temperature, generator winding temperature, generator bearing temperature, gearbox bearing temperature, oil pressure, generator output, and inlet guide vane position.

14. The control system of claim 12, wherein said means of inputting setpoint data is a keyboard.

15. The control system of claim 12, wherein said means of inputting setpoint data is a touch screen.

16. The control system of claim 12, wherein said fuel control valve controls a supply of liquid fuel.

17. The control system of claim 12, wherein said fuel control valve controls a supply of gaseous fuel.

18. The control system of claim 12, wherein said compression relief system employs at least one solenoid valve in communication with said software, said solenoid valve adapted, in response to a signal from said software, to allow the transfer of air from said combustion section of said gas turbine engine to the atmosphere.

19. The control system of claim 12, wherein said compression relief system employs at least one solenoid valve in communication with said software, said solenoid valve adapted, in response to a signal from said software, to allow the transfer of air from said combustion section of said gas turbine engine to a collection device.

20. The control system of claim 12, wherein said air directing system employs an electromechanical actuator, in communication with said software.

21. The control system of claim 20, wherein said electromechanical actuator is coupled to a set of inlet guide vanes within said gas turbine engine.

22. The control system of claim 20, further comprising a microprocessor on said electromechanical actuator for controlling the movement thereof in response to a signal from said software.

23. The control system of claim 12, wherein said software is adapted to provide predictive modeling.