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A combustor assembly in a gas turbine engine includes a combustor device, a fuel injection system, a transition duct, and an intermediate duct. The combustor device includes a flow sleeve for receiving pressurized air and a liner surrounded by the flow sleeve. The fuel injection system provides fuel

A combustor assembly in a gas turbine engine includes a combustor device, a fuel injection system, a transition duct, and an intermediate duct. The combustor device includes a flow sleeve for receiving pressurized air and a liner surrounded by the flow sleeve. The fuel injection system provides fuel to be mixed with the pressurized air and ignited in the liner to create combustion products. The intermediate duct is disposed between the liner and the transition duct so as to define a path for the combustion products to flow from the liner to the transition duct. The intermediate duct is associated with the liner such that movement may occur therebetween, and the intermediate duct is associated with the transition duct such that movement may occur therebetween. The flow sleeve includes structure that defines an axial stop for limiting axial movement of the intermediate duct.

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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 flow sleeve coupled to said main casing for receiving pressurized air, wherein an aft end of said flow sleeve defines an air inlet t

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 flow sleeve coupled to said main casing for receiving pressurized air, wherein an aft end of said flow sleeve defines an air inlet that receives the pressurized air from a combustor plenum located about said combustor assembly; anda liner surrounded by said flow sleeve and having an inlet, an outlet, and an inner volume;a first fuel injection system associated with said flow sleeve for providing fuel that is adapted to be mixed with at least a portion of the pressurized air and ignited in said liner inner volume to create combustion products that define first working gases;a transition duct having an inlet section and an outlet section that discharges gases to a turbine section; andan intermediate duct upstream of said transition duct and 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 movement may occur between said intermediate duct and said liner;said intermediate duct outlet portion is associated with said transition duct inlet section such that movement may occur between said intermediate duct and said transition duct; andsaid flow sleeve includes structure that defines an axial stop for limiting axial movement of said intermediate duct and wherein said air inlet is positioned about said intermediate duct. 2. A combustor assembly as set out in claim 1, further comprising a second fuel injection system comprising at least one fuel injector that injects fuel into said intermediate duct where the fuel injected by said at least one fuel injector mixes with remaining pressurized air and ignites to define further combustion products defining second working gases. 3. A combustor assembly as set out in claim 1, wherein said structure of said flow sleeve that defines said axial stop comprises at least one axial movement restraint structure that extends radially inwardly from said flow sleeve at a predefined axial location and prevents axial movement of said intermediate duct beyond said predefined axial location. 4. A combustor assembly as set out in claim 3, wherein said transition duct defines a second axial stop for preventing axial movement of said intermediate duct beyond an axial location of said second axial stop. 5. A combustor assembly as set out in claim 4, wherein said second axial stop is defined by a radially inwardly extending portion of said transition duct that contacts said outlet portion of said intermediate duct to prevent axial movement of said intermediate duct beyond the axial location of said second axial stop. 6. A combustor assembly as set out in claim 1, wherein said structure of said flow sleeve that defines said axial stop comprises a radially inwardly tapered portion of said flow sleeve that contacts a tapered transitional portion of said intermediate duct to prevent further axial movement of said transitional portion of said intermediate duct beyond said tapered portion of said flow sleeve. 7. A combustor assembly as set out in claim 6, wherein said liner defines a second axial stop for preventing axial movement of said intermediate duct beyond an axial location of said second axial stop. 8. A combustor assembly as set out in claim 7, wherein said second axial stop is defined by said outlet of said liner and contacts said transitional portion of said intermediate duct to prevent further axial movement of said transitional portion of said intermediate duct beyond the axial location of said second axial stop. 9. A combustor assembly as set out in claim 1, wherein a first spring clip structure is provided on one of said liner outlet and said intermediate duct inlet portion such that a friction fit coupling is provided between said liner and said intermediate duct and wherein a second spring clip structure is provided on one of said intermediate duct outlet portion and said transition duct inlet section such that a friction fit coupling is provided between said intermediate duct and said transition duct. 10. A combustor assembly as set out in claim 1, wherein said flow sleeve has an inner surface and said intermediate duct has an outer surface and pressurized air passes through a gap defined between said flow sleeve inner surface and said intermediate duct outer surface. 11. 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 flow sleeve coupled to said main casing for receiving pressurized air, wherein an aft end of said flow sleeve defines an air inlet that receives the pressurized air from a combustor plenum located about said combustor assembly; anda liner surrounded by said flow sleeve and having an inlet, an outlet, and an inner volume;a first fuel injection system associated with said flow sleeve for providing fuel that is adapted to be mixed with at least a portion of the pressurized air and ignited in said liner inner volume to create combustion products that define first working gases;a transition duct having an inlet section and an outlet section that discharges gases to a turbine section; andan intermediate duct upstream of said transition duct and 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 movement may occur between said intermediate duct and said liner;said intermediate duct outlet portion is associated with said transition duct inlet section such that movement may occur between said intermediate duct and said transition duct;said flow sleeve includes structure that defines a first axial stop for limiting axial movement of said intermediate duct; andsaid transition duct defines a second axial stop for limiting axial movement of said intermediate duct and wherein said air inlet is positioned about said intermediate duct. 12. A combustor assembly as set out in claim 11, wherein said second axial stop is defined by a radially inwardly extending portion of said transition duct that contacts said outlet portion of said intermediate duct to prevent axial movement of said intermediate duct beyond an axial location of said second axial stop. 13. A combustor assembly as set out in claim 12, wherein said structure of said flow sleeve that defines said first axial stop comprises at least one axial movement restraint structure that extends radially inwardly from said flow sleeve at a predefined axial location and prevents axial movement of said intermediate duct beyond said predefined axial location. 14. A combustor assembly as set out in claim 13, further comprising a second fuel injection system comprising at least one fuel injector that injects fuel into said intermediate duct where the fuel injected by said at least one fuel injector mixes with remaining pressurized air and ignites to define further combustion products defining second working gases. 15. 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 flow sleeve coupled to said main casing for receiving pressurized air, wherein an aft end of said flow sleeve defines an air inlet that receives the pressurized air from a combustor plenum located about said combustor assembly; anda liner surrounded by said flow sleeve and having an inlet, an outlet, and an inner volume;a first fuel injection system associated with said flow sleeve for providing fuel that is adapted to be mixed with at least a portion of the pressurized air and ignited in said liner inner volume to create combustion products that define first working gases;a transition duct having an inlet section and an outlet section that discharges gases to a turbine section; andan intermediate duct upstream of said transition duct and 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 movement may occur between said intermediate duct and said liner;said intermediate duct outlet portion is associated with said transition duct inlet section such that movement may occur between said intermediate duct and said transition duct;said flow sleeve includes structure that defines a first axial stop for limiting axial movement of said intermediate duct; andsaid liner defines a second axial stop for limiting axial movement of said intermediate duct and wherein said air inlet is positioned about said intermediate duct. 16. A combustor assembly as set out in claim 15, wherein said second axial stop is defined by said outlet of said liner and contacts said a tapered transitional portion of said intermediate duct to prevent further axial movement of said transitional portion of said intermediate duct beyond an axial location of said second axial stop. 17. A combustor assembly as set out in claim 16, wherein said structure of said flow sleeve that defines said first axial stop comprises a radially inwardly tapered portion of said flow sleeve that contacts said tapered transitional portion of said intermediate duct to prevent further axial movement of said transitional portion of said intermediate duct beyond said tapered portion of said flow sleeve. 18. A combustor assembly as set out in claim 17, further comprising a second fuel injection system comprising at least one fuel injector that injects fuel into said intermediate duct where the fuel injected by said at least one fuel injector mixes with remaining pressurized air and ignites to define further combustion products defining second working gases. 19. A combustor assembly as set out in claim 1, wherein said flow sleeve is coupled to said main casing via a cover plate that provides a direct coupling between said flow sleeve and said main casing.