Gas turbine engine including secondary combustion chamber integrated with the stator vanes in the turbine/expansion section of the engine and a method of operating the same

摘要

A combustor system for use in a turbine engine is provided. The turbine engine includes turbine assembly that includes a fluid inlet, a fluid outlet, and a combustion gas path defined therebetween. The combustor system includes a first combustor assembly and a second combustor assembly. The first combustor assembly is coupled to the turbine assembly for channeling a first flow of combustion gases through the turbine assembly. The first combustor assembly is oriented adjacent to the turbine assembly inlet to channel the first flow of combustion gases to the turbine assembly through the turbine assembly inlet. The second combustor assembly is coupled to the turbine assembly along the combustion gas path for channeling a second flow of combustion gases through the turbine assembly.

主权项

1. A combustor system for use in a turbine engine including a turbine assembly that includes a fluid inlet, a fluid outlet, and a combustion gas path defined therebetween, said combustor system comprising:
a first combustor assembly coupled to the turbine assembly for channeling a first flow of combustion gases through the turbine assembly, said first combustor assembly oriented adjacent to the turbine assembly inlet to channel the first flow of combustion gases to the turbine assembly through the turbine inlet; a second combustor assembly coupled to the turbine assembly along the combustion gas path for channeling a second flow of combustion gases through the turbine assembly; and a fuel assembly comprising a fuel reformer that treats a fuel from a fuel supply to generate a fuel mixture, a fuel separator that separates the fuel mixture into a first fuel flow and second fuel flow, wherein the first fuel flow is different than the second fuel flow, and a flow control assembly that channels the first fuel flow to the first combustor assembly and channels the second fuel flow to said second combustor assembly.