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    Dual wall combustor liner
    21.
    发明公开
    Dual wall combustor liner 有权
    dop el。ige。

    公开(公告)号：EP1801502A2

    公开(公告)日：2007-06-27

    申请号：EP06255405.0

    申请日：2006-10-20

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Burd, Steven W. ,  Kramer, Stephen K. ,  Ols, John T.

    IPC: F23R3/00

    CPC classification number: F23R3/002 ,  F23R3/007 ,  F23R2900/00017 ,  F23R2900/03044

    Abstract: A combustor liner assembly (10) includes an outer shell (14) made of a ceramic composite and an inner heat shell (16) that is supported within the outer shell (14). The inner heat shield (16) defines a surface that is exposed to combustion gases. The inner heat shield (16) is made of material that is compatible with the ceramic matrix composite and that provides favorable thermal gradient capability for a combustion chamber.

    Abstract translation: 燃烧器衬套组件（10）包括由陶瓷复合材料制成的外壳（14）和支撑在外壳（14）内的内热壳体（16）。 内部隔热罩（16）限定了暴露于燃烧气体的表面。 内部隔热罩（16）由与陶瓷基体复合材料相容的材料制成，为燃烧室提供有利的热梯度能力。

    Method of combustion with a two stream tangential entry nozzle
    24.
    发明公开
    Method of combustion with a two stream tangential entry nozzle 失效
    与切向Zweistromdüse燃烧过程

    公开(公告)号：EP0849527A3

    公开(公告)日：1999-06-09

    申请号：EP97310459.9

    申请日：1997-12-22

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Kramer, Stephen K. ,  Morford, Stephen A. ,  Graves, Charles B.

    IPC: F23C7/00 ,  F23D17/00

    CPC classification number: F23C7/002 ,  F05B2250/322 ,  F23C2900/07002 ,  F23D17/002 ,  F23D2206/10

    Abstract: A method for burning fuel in the combustor of a gas turbine engine with a premixing type of combustion which comprises providing a scroll swirler (14) having first and second endplates (16,18), the first endplate is spaced relation to the second endplate defining a substantially cylindrical mixing zone (28) therebetween, the second endplate having a combustor inlet port (20) extending therethrough, providing a centerbody (12) located within the mixing zone and having a radially outer surface that tapers toward the combustor inlet and extends substantially the entire length of the mixing zone, introducing a first portion of combustion air tangentially into the mixing zone substantially continuously along the length thereof, introducing a first portion of fuel into the combustion air as the combustion air is introduced into the mixing zone, mixing the combustion air and fuel by swirling the combustion air and fuel about the centerbody while flowing the combustion air and fuel towards the combustor inlet, flowing the first portion of combustion air into the combustor inlet, introducing a second portion of combustion air into the first portion radially inward thereof at the combustor inlet, the sum of the first and second portions of combustion air defining total airflow, and the second portion of combustion air equal to 85-89% of the total airflow, and burning the fuel external of the mixing zone.

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