Method for gas turbine light-off

• US 6,810,677 B2
• Filed: 08/27/2002
• Issued: 11/02/2004
• Est. Priority Date: 08/27/2001
• Status: Expired due to Fees

• Current Assignee: Capstone Turbine Corp.
• Original Assignee: Elliott Energy Systems, Inc.
• Inventors: Dewis, David
• Primary Examiner(s): Casaregola, Louis J.
• Application Number:
  US10/229,383
• Publication Number:
  US 20030056521A1
• Time in Patent Office: 798 Days
• Field of Search: 607/73, 607/78, 607/86, 607/87, 607/88, 607/40
• US Class Current: 60/778
• CPC Class Codes: F02C 7/26 Starting; Ignition
• CPC Class Codes: F02C 7/264 Ignition
• CPC Class Codes: F02C 9/26 Control of fuel supply F02C9/48 takes precedence; fuel valves F02C7/232
• CPC Class Codes: F05D 2260/85 Starting
• CPC Class Codes: F05D 2270/04 to control acceleration (u)
• CPC Class Codes: F05D 2270/0831 indirectly, at the exhaust
• CPC Class Codes: F05D 2270/303 Temperature

Abstract

A method for gas turbine light-off that utilizes a fixed or secondary fuel line that provides a substantially constant flow of fuel to the combustor primarily upon light-off.

Claims

1. A method for light-off of a gas turbine engine comprising:

a. determining ambient conditions and fuel heating value;

b. accelerating a gas turbine engine at a preset acceleration rate to a speed to provide a supply of combustion air to a combustor for light-off of said gas turbine engine, wherein said preset acceleration rate of said gas turbine engine is determined based upon said ambient conditions and said fuel heating value;

c. activating an ignition source for said combustor of said gas turbine engine; and

d. initiating a flow of fuel to said combustor at a substantially constant rate via a fuel line to provide an optimum supply of fuel to said combustor and maintaining said constant rate until the correct fuel-to-air ratio is achieved and light-off of said gas turbine engine occurs.

2. The method as claimed in claim 1, wherein said ambient conditions comprise ambient temperature and atmospheric pressure.

3. The method as claimed in claim 1, wherein said gas turbine engine is accelerated by applying electrical assistance.

5. The method as claimed in claim 1, further comprising sensing for light-off after step c by using a heat sensor.

6. The method as claimed in claim 1, further comprising sensing for light-off after step c by measuring exhaust gas temperature of said gas turbine engine.

7. The method as claimed in claim 1, wherein said fuel line comprises a valve for fixing the flow of fuel through said fuel line.

8. The method as claimed in claim 7, wherein said fuel line further comprises a flow orifice for fixing the flow of fuel through said fuel line.

9. The method as claimed in claim 3, further comprising eliminating said electrical assistance to said gas turbine engine based upon a fixed value of said speed of said gas turbine engine.

4. A method for light-off of a gas turbine engine comprising:

a. accelerating a gas turbine engine at a preset acceleration rate to a speed to provide a supply of combustion air to a combustor for light-off of said gas turbine engine;

b. determining ambient conditions and fuel heating value;

c. activating an ignition source for said combustor of said gas turbine engine, wherein said ignition source is activated based upon said ambient conditions and said speed of said gas turbine engine,

d. initiating a flow of fuel to said combustor at a substantially constant rate via a fuel line to provide an optimum supply of fuel to said combustor and maintaining said constant rate until the correct fuel-to-air ratio is achieved and light-off of said gas turbine engine occurs.

10. A method for light-off of a gas turbine engine comprising:

a. accelerating a gas turbine engine at a preset acceleration rate to a speed to provide a supply of combustion air to a combustor for light-off of said gas turbine engine;

b. activating an ignition source for said combustor of said gas turbine engine;

c. initiating a flow of fuel to said combustor at a substantially constant rate via a secondary fuel line to provide an optimum supply of fuel to said combustor and maintaining said constant rate until the correct fuel-to-air ratio is achieved and light-off of said gas turbine engine occurs; and

d. initiating a flow of fuel to said combustor via a primary fuel line after light-off has occurred, and ramping up said flow of fuel to said combustor of said gas turbine engine to increase said speed of said gas turbine engine to a final speed to which a load is applied.

11. The method as claimed in claim 10, further comprising determining ambient conditions and fuel heating value, wherein said preset acceleration rate of said gas turbine engine is determined based upon said ambient conditions and said fuel heating value.

12. The method as claimed in claim 10, wherein said gas turbine engine is accelerated by applying electrical assistance.

13. The method as claimed in claim 11, wherein said ignition source is activated based upon said ambient conditions and said speed of said gas turbine engine.

14. The method as claimed in claim 10, further comprising sensing for ignition after step c by measuring exhaust gas temperature of said gas turbine engine.

15. The method as claimed in claim 12, further comprising eliminating said electrical assistance to said gas turbine engine based upon a fixed value of said speed of said gas turbine engine.

16. The method as claimed in claim 10, wherein said primary fuel line comprises a control valve for ramping up fuel flow to said combustor of said gas turbine engine.

17. A method for light-off of a gas turbine engine comprising:

a. determining ambient conditions and fuel heating value;

b. setting an acceleration rate of a gas turbine engine based upon said ambient conditions and said fuel heating value;

c. applying electrical assistance to accelerate said gas turbine engine at said acceleration rate, whereby a turbine drive shaft rotates causing compressor blades and turbine blades to rotate;

d. activating an ignition source for a combustor of said gas turbine engine;

e. supplying a flow of fuel to said combustor of said gas turbine engine at a substantially constant rate via a secondary fuel line until light-off of said gas turbine engine occurs;

f. sensing for ignition of said gas turbine engine;

g. eliminating said electrical assistance to said gas turbine engine after ignition has occurred based upon a fixed value of a speed of said turbine blades; and

i. initiating a flow of fuel to said combustor via a primary fuel line and ramping up said flow of fuel to said combustor of said gas turbine engine to increase said speed of said gas turbine engine to a final speed to which a load is applied.