Patent ID: 9353691
Filing Date: 2016-05-31
CPC Classification: F02C,F05D,F23K,F23R

Claim Text:
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; 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, 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.