FUEL ROUTING SYSTEM OF A GAS TURBINE ENGINE AND METHOD OF ROUTING FUEL

• US 20140165580A1
• Filed: 12/18/2012
• Published: 06/19/2014
• Est. Priority Date: 12/18/2012
• Status: Active Grant

• Current Assignee: GE Infrastructure Technology, LLC (General Electric Company)
• Original Assignee: General Electric Company
• Inventors: Shinkle, William Randolph, Simmons, James Arthur
• Granted Patent: US 9,353,691 B2
• Time in Patent Office: Days
• US Class Current: 60/772
• CPC Class Codes: F02C 7/22 Fuel supply systems
• CPC Class Codes: F02C 7/222 Fuel flow conduits, e.g. manifolds
• CPC Class Codes: F02C 7/228 Dividing fuel between various burners
• CPC Class Codes: F02C 9/263 by means of fuel metering valves
• 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: F02C 9/34 Joint control of separate flows to main and auxiliary burners
• CPC Class Codes: F05D 2220/76 an electrical generator
• CPC Class Codes: F23K 2300/20 Supply line arrangements
• CPC Class Codes: F23K 5/06 from a central source to a plurality of burners
• CPC Class Codes: F23K 5/14 Details thereof
• CPC Class Codes: F23R 3/34 Feeding into different combustion zones

Abstract

A fuel routing system of a gas turbine engine includes a primary fuel circuit in communication with a fuel source and a fuel distribution manifold. Also included is a secondary fuel circuit extending from the primary fuel circuit to a plurality of fuel nozzles configured to direct fuel to a plurality of combustor chambers. Further included is a main fuel flow control valve disposed in the primary fuel circuit for restricting a fuel flow to the fuel distribution manifold upon removal of an electrical load operably coupled to the gas turbine engine. Yet further included is a plurality of check valves disposed between the secondary fuel circuit and the primary fuel circuit for restricting the fuel flow between the secondary fuel circuit and the primary fuel circuit.

Claims

1. A fuel routing system of a gas turbine engine comprising:

a primary fuel circuit feeding a fuel distribution manifold which directs fuel to a combustor chamber;

a secondary fuel circuit extending from the primary fuel circuit to a plurality of fuel nozzles configured to direct fuel to the combustor chamber;

a main fuel flow control valve disposed in the primary fuel circuit for restricting a fuel flow to the fuel distribution manifold upon removal of an electrical load operably coupled to the gas turbine engine; and

a plurality of check valves located between the secondary fuel circuit and the primary fuel circuit for restricting the fuel flow from the secondary fuel circuit to the primary fuel circuit.

2. The fuel routing system of claim 1, wherein the secondary fuel circuit comprises a plurality of fuel lines each in communication with one of the plurality of fuel nozzles.

3. The fuel routing system of claim 1, wherein the plurality of fuel nozzles comprises a portion of a total number of fuel nozzles of the gas turbine engine.

4. The fuel routing system of claim 3, wherein the portion of the total number of fuel nozzles is a subset of the total number of fuel nozzles.

5. The fuel routing system of claim 1, further comprising a vent line extending from the primary fuel circuit and extending to a location configured to vent contents of the primary fuel circuit to atmosphere.

6. The fuel routing system of claim 5, further comprising a blowoff valve disposed in the vent line, the blowoff valve in an open state during a closed condition of the main fuel flow control valve.

7. The fuel routing system of claim 5, wherein the vent line is disposed between the main fuel flow control valve and the fuel distribution manifold.

8. The fuel routing system of claim 1, further comprising at least one flame detector proximate the fuel distribution manifold for detecting burning from at least one fuel nozzle.

9. The fuel routing system of claim 8, wherein the plurality of fuel nozzles in communication with the secondary fuel circuit are disposed proximate the at least one flame detector.

10. The fuel routing system of claim 3, wherein the total number of fuel nozzles comprises about 10 fuel nozzles to about 100 fuel nozzles.

11. The fuel routing system of claim 1, wherein the plurality of fuel nozzles comprises about 8 fuel nozzles to about 18 fuel nozzles.

12. A method of routing fuel in a gas turbine engine comprising:

determining that an electrical load operably coupled to the gas turbine engine has been removed;

closing a main fuel flow control valve for restricting a fuel flow along a primary fuel circuit to a fuel distribution manifold; and

routing a fuel to a secondary fuel circuit in communication with a plurality of fuel nozzles comprising a portion of a total number of fuel nozzles of the gas turbine engine.

13. The method of claim 12, wherein the plurality of fuel nozzles comprises a subset of the total number of fuel nozzles to achieve a reduced overall effective area for fuel injection.

14. The method of claim 12, further comprising restricting the fuel flow between the primary fuel circuit and a plurality of fuel lines of the secondary fuel circuit by closing a plurality of check valves disposed between each of the plurality of fuel lines and the primary fuel circuit.

15. The method of claim 12, further comprising opening a blowoff valve disposed in a vent line during a closed condition of the main fuel flow control valve.

16. The method of claim 12, further comprising selecting which of the total number of fuel nozzles comprise the plurality of fuel nozzles.

17. The method of claim 16, wherein selecting the plurality of fuel nozzles in close proximity to at least one flame detector disposed proximate the fuel distribution manifold.