초록 ▼

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 pluralit

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.

대표청구항 ▼

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 an upstream location of the primary fuel circuit to a plurality of fuel nozzles configured to dir

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 an upstream location of the primary fuel circuit to a plurality of fuel nozzles configured to direct fuel to the combustor chamber, the secondary fuel circuit including a single fuel line that branches into a plurality of fuel lines that feed the plurality of fuel nozzles;a main fuel flow control valve disposed in the primary fuel circuit, the main fuel flow control valve restricting a fuel flow to the fuel distribution manifold upon removal of an electrical load operably coupled to the gas turbine engine; anda 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, the plurality of check valves being located on a plurality of fuel passages directly connecting a downstream location of the primary fuel circuit to the plurality of fuel lines. 2. The fuel routing system of claim 1, wherein each one of the plurality of fuel lines is 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 3, wherein the total number of fuel nozzles comprises about 10 fuel nozzles to about 100 fuel nozzles. 6. 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 the atmosphere. 7. The fuel routing system of claim 6, 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. 8. The fuel routing system of claim 6, wherein the vent line is disposed between the main fuel flow control valve and the fuel distribution manifold. 9. 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. 10. The fuel routing system of claim 9, wherein the plurality of fuel nozzles in communication with the secondary fuel circuit are disposed proximate the at least one flame detector. 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 within the fuel routing system of claim 1 in a gas turbine engine comprising: determining that the electrical load operably coupled to the gas turbine engine has been removed;closing the main fuel flow control valve; androuting a fuel to the secondary fuel circuit. 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 the plurality of fuel lines of the secondary fuel circuit by closing the 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 the plurality of fuel nozzles is in close proximity to at least one flame detector proximate the fuel distribution manifold.