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
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United States of America Patent
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Sep 1, 2015
Grant Date -
Jul 4, 2013
app pub date -
Dec 29, 2011
filing date -
Dec 29, 2011
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Abstract
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.
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