Patent ID: 9366184
Filing Date: 2016-06-14
CPC Classification: F02C,F23R

Claim Text:
1. A gas turbine engine, comprising: a compressor for compressing air; a combustor for generating a post combustion gas by combusting a compressed air exiting from the compressor; a first turbine for expanding the post combustion gas; a splitting zone including one or more aerodynamically shaped flow diverters configured to split an expanded combustion gas exiting from the first turbine into a first stream, a second stream and a third stream; a reheat combustor for combusting the first stream of the expanded combustion gas; a pressure loss device for developing a pressure differential between the second stream and the third stream, wherein an outer liner and one or more flame stabilizers of the reheat combustor are cooled using the second stream of the expanded combustion gas and an inner liner of the reheat combustor is cooled using the third stream of the expanded combustion gas and a portion of the second stream of the expanded combustion gas exiting the one or more flame stabilizers; and a second turbine for expanding a combusted first stream of expanded combustion gas from the reheat combustor.