Combustor assembly in a gas turbine engine
First Claim
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 for receiving pressurized air; and
a liner disposed radially inwardly from said flow sleeve having an inlet, an outlet and an inner volume;
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.
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Accused Products
Abstract
A combustor assembly in a gas turbine engine. The combustor assembly includes a combustor device coupled to a main engine casing, a first fuel injection system, a transition duct, and an intermediate duct. The combustor device includes a flow sleeve for receiving pressurized air and a liner disposed radially inwardly from the flow sleeve. The first fuel injection system provides fuel that is ignited with the pressurized air creating first working gases. The intermediate duct is disposed between the liner and the transition duct and defines a path for the first working gases to flow from the liner to the transition duct. An intermediate duct inlet portion is associated with a liner outlet and allows movement between the intermediate duct and the liner. An intermediate duct outlet portion is associated with a transition duct inlet section and allows movement between the intermediate duct and the transition duct.
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Citations
16 Claims
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1. A combustor assembly in a gas turbine engine comprising a main casing, the combustor assembly comprising:
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a combustor device coupled to the main casing comprising; a flow sleeve for receiving pressurized air; and a liner disposed radially inwardly from said flow sleeve having an inlet, an outlet and an inner volume; 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. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9)
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10. A combustor assembly in a gas turbine engine comprising a main casing, the combustor assembly comprising:
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a combustor device coupled to the main casing comprising; a flow sleeve for receiving pressurized air; and a liner disposed radially inwardly from said flow sleeve having an inlet, an outlet and an inner volume; a transition duct downstream of an intermediate duct and having an inlet section and an outlet section that discharges gases to a turbine section; the intermediate duct having inlet and outlet portions and disposed between said liner and 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; and a fuel injection system associated with said intermediate duct to inject fuel into said intermediate duct where the fuel mixes with pressurized air and ignites to define combustion products defining working gases, wherein said flow sleeve surrounds said liner and said intermediate duct is integral with said flow sleeve. - View Dependent Claims (11, 12, 13, 14, 15, 16)
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Specification