Systems and Methods for Rapid Turbine Deceleration

• US 20100275608A1
• Filed: 06/30/2010
• Published: 11/04/2010
• Est. Priority Date: 05/04/2009
• Status: Abandoned Application

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: Snider, David August, Memmer, John David
• Application Number:
  US12/826,733
• Publication Number:
  US 20100275608A1
• Time in Patent Office: Days
• US Class Current: 60/772
• 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: F01D 21/14 responsive to other specific conditions
• CPC Class Codes: F02C 7/268 Starting drives for the rotor , acting directly on the rotor of the gas turbine to be started
• CPC Class Codes: F02C 9/48 Control of fuel supply conjointly with another control of the plant with nozzle section control F02K1/17
• CPC Class Codes: F02C 9/56 with power transmission control
• CPC Class Codes: F05D 2220/76 an electrical generator
• CPC Class Codes: F05D 2260/85 Starting
• CPC Class Codes: F05D 2260/903 using electrical or magnetic forces
• CPC Class Codes: F05D 2270/304 Spool rotational speed

Abstract

The present application provides for a gas turbine engine system for turbine deceleration during shutdown procedures. The gas turbine engine system may include a rotor extending through a turbine, a generator engaged with the rotor, and a starting system in communication with the rotor. The starting system may reverse the operation of the generator so as to apply torque to the rotor during the shutdown procedures.

Claims

1. A gas turbine engine system for turbine deceleration during shutdown procedures, comprising:

a rotor extending through a turbine;

a generator engaged with the rotor; and

a starting system in communication with the rotor;

wherein the starting system reverses operation of the generator so as to apply torque to the rotor during the shutdown procedures.

2. The gas turbine engine system of claim 1, further comprising a compressor in communication with the rotor for producing a flow of air.

3. The gas turbine engine system of claim 2, wherein reversing the operation of the generator so as to apply torque to the rotor limits the flow of air over the rotor.

4. The gas turbine engine system of claim 2, wherein reversing the operation of the generator so as to apply torque to the rotor limits the flow of air through the turbine.

5. The gas turbine engine system of claim 1, further comprising a heat recovery steam generator down steam of the turbine.

6. The gas turbine engine system of claim 5, wherein reversing the operation of the generator so as to apply torque to the rotor limits the flow of air through the heat recovery steam generator.

7. The gas turbine engine system of claim 1, wherein the starting system comprises a load commutating inverter in communication with the generator.

8. The gas turbine engine system of claim 1, further comprising a combustor and wherein a flow of fuel is reduced as or before the generator applies torque to the rotor.

9. A method for shutting down a gas turbine engine system, comprising:

reducing a flow of fuel to a combustor;

reversing the operation of a generator so as to apply torque to a rotor; and

increasing the deceleration of the rotor so as to limit a flow of air into the gas turbine engine system.

10. The method of claim 9, wherein the step of reversing the operation of a generator comprises using a starting means in a regenerative mode.

11. The method of claim 9, wherein the step of reversing the operation of a generator comprising operating a load commutating inverter.

12. The method of claim 9, wherein the step of increasing the deceleration of the rotor so as to limit a flow of air into the gas turbine engine system comprises limiting the flow of air about the rotor.

13. The method of claim 9, wherein the step of increasing the deceleration of the rotor so as to limit a flow of air into the gas turbine engine system comprises limiting the flow of air through a turbine.

14. The method of claim 9, wherein the step of increasing the deceleration of the rotor so as to limit a flow of air into the gas turbine engine system comprises limiting the flow of air through a heat recovery steam generator.

15. A gas turbine engine system for turbine deceleration during shutdown procedures, comprising:

a rotor extending through a turbine;

a compressor in communication with the rotor for producing a flow of air;

a generator engaged with the rotor; and

a starting system in communication with the rotor;

wherein the starting system reverses operation of the generator via a load commutating inverter so as to apply torque to the rotor during the shutdown procedures so as to limit the flow of air.

16. The gas turbine engine system of claim 15, wherein reversing the operation of the generator so as to apply torque to the rotor limits the flow of air over the rotor.

17. The gas turbine engine system of claim 15, wherein reversing the operation of the generator so as to apply torque to the rotor limits the flow of air through the turbine.

18. The gas turbine engine system of claim 15, further comprising a heat recovery steam generator down steam of the turbine.

19. The gas turbine engine system of claim 18, wherein reversing the operation of the generator so as to apply torque to the rotor limits the flow of air through the heat recovery steam generator.

20. The gas turbine engine system of claim 15, further comprising a combustor and wherein a flow of fuel is reduced as or before the generator apply torque to the rotor.