Patent ID: 8375726
Filing Date: 2013-02-19
Classification: F23R

Abstract:
1. A combustor assembly in a gas turbine engine comprising a main casing, the combustor assembly comprising: a combustor device coupled to the main casing comprising: a first fuel injection system associated with said flow sleeve for providing fuel which is adapted to be mixed with at least a portion of the pressurized air and ignited in said liner inner volume creating combustion products defining first working gases; a transition duct downstream of an intermediate duct and having an inlet section and an outlet section that discharges gases to a turbine section; and the intermediate duct having inlet and outlet portions and disposed between said liner and said transition duct so as to define a path for the first working gases to flow from said liner to said transition duct, wherein said intermediate duct inlet portion is associated with said liner outlet such that substantially unconstrained axial movement occurs between said intermediate duct and said liner and said intermediate duct outlet portion is associated with said transition duct inlet section such that substantially unconstrained axial movement occurs between said intermediate duct and said transition duct, wherein said flow sleeve surrounds said liner and said intermediate duct is integral with said flow sleeve.