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    INVASION-RESISTANT FAN CASING FOR TURBINE ENGINE
    1.
    发明专利
    INVASION-RESISTANT FAN CASING FOR TURBINE ENGINE 失效

    公开(公告)号：JPH11324615A

    公开(公告)日：1999-11-26

    申请号：JP11186099

    申请日：1999-04-20

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： COSTA MARK W ,  FOOSE ANDREW S ,  KORN NATHAN D ,  KOWZA JAN B ,  LOPARDI WENDY P ,  WELCH DOUGLAS A

    IPC: F01D21/04 ,  F01D25/24 ,  F02C7/04

    Abstract: PROBLEM TO BE SOLVED: To provide an invasion-resistant fan casing for a turbine engine. SOLUTION: Broken pieces separated from a fan blade 16 are housed by a fan casing 12 for a turbine engine of invasion resistance property. The casing is provided with a supporting body case 14 invaded easily, and an invasion enable cover 32 for enclosing a shock region 1 of a supporting body cover 34 and which is offset from the shock region. A housing cover 36 encloses both of the invasion enable cover 32 and the supporting body cover 34. The housing cover 36 is formed as aromatic polyamide fiber woven fabric, and the supporting body cover 34 is formed as aggregate cell alley.

    6.
    发明专利
    未知

    公开(公告)号：DE69931554T2

    公开(公告)日：2007-01-18

    申请号：DE69931554

    申请日：1999-04-14

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： COSTA MARK W ,  FOOSE ANDREW S ,  KORN NATHAN D ,  KOWZA JAN B ,  LOPARDI WENDY P ,  WELCH DOUGLAS A

    IPC: F01D25/24 ,  F01D21/04 ,  F02C7/04 ,  F02K3/04

    Abstract: A penetration resistant turbine engine fan casing (12) for containing separated fragments of a fan blade (16) includes a penetration susceptible support case (14), a penetrable covering (32) circumscribing an impact zone (I) of the support case and an optional collapsible support covering (34) circumscribing the case but axially offset from the impact zone. A containment covering (36) circumscribes both the penetrable covering (32) and the support covering (34). In a preferred embodiment, the coverings are aromatic polyamide fiber fabrics and the support covering is a collapsible cellular array. In operation, a detached fragment of a fan blade penetrates through the case (14) and the penetrable covering (32), and is plastically deformed by the penetrable covering to reduce the fragment's potential for damaging the containment covering (36). The containment covering intercepts the deformed fragment, confining it to a predetermined radial envelope bounded by the inner surface (58) of a nacelle (52). The impact forces arising from a separated blade fragment cause the containment fabric to collapse the cellular array (32) and momentarily detension the containment fabric to maximize its penetration resistance.

    AUXILIARY COMPONENT MOUNTS
    8.
    发明申请
    AUXILIARY COMPONENT MOUNTS 审中-公开
    辅助部件支架

    公开(公告)号：WO2014081500A3

    公开(公告)日：2014-08-21

    申请号：PCT/US2013059746

    申请日：2013-09-13

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： ROBERTSON THOMAS J ,  CLARKSON STEVEN ,  COSTA MARK W

    IPC: F16M13/00

    CPC classification number: F02C7/32 ,  F01D21/045 ,  F02C7/20 ,  F05D2220/32 ,  F05D2240/90 ,  F05D2260/30 ,  F05D2260/311

    Abstract: A mount for mounting a component to a gas turbine engine is disclosed. The mount may include a central portion that attaches to the component, and a flange circumscribing the central portion and extending to the gas turbine engine, the flange including a fusible region that breaks at a predetermined load. A method for protecting a component mounted to a gas turbine engine is also disclosed. The method may include attaching a mount to a casing of the gas turbine engine, the mount including a fusible region that breaks at a predetermined load. The method may further include attaching the component to the mount. The method may further include the fusible region breaking when the mount experiences the predetermined load, detaching the component from the casing of the gas turbine engine.

    Abstract translation: 公开了一种用于将部件安装到燃气涡轮发动机的支架。 所述安装件可以包括附接到所述部件的中央部分和限定所述中央部分并且延伸到所述燃气涡轮发动机的凸缘，所述凸缘包括在预定载荷下断裂的可熔区域。 还公开了一种用于保护安装到燃气涡轮发动机的部件的方法。 该方法可以包括将安装件附接到燃气涡轮发动机的壳体，安装件包括在预定负载下断裂的可熔区域。 该方法可以进一步包括将部件附接到安装件。 该方法可进一步包括当安装件经历预定负载时可熔区断裂，从燃气涡轮发动机的壳体分离该部件。

    DUST LINER ACOUSTIC SPLICE
    9.
    发明专利
    DUST LINER ACOUSTIC SPLICE 未知

    公开(公告)号：CA2537643A1

    公开(公告)日：2006-10-22

    申请号：CA2537643

    申请日：2006-02-22

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： COSTA MARK W ,  BROWN CHARLES W ,  FREILER CHRIS

    IPC: F01D25/24 ,  F02C7/045 ,  F02K99/00 ,  G10K11/16

    Abstract: A duct liner assembly includes a noise attenuation layer for absorbing noi se energy that is covered by a face sheet. The face sheet includes a seam that is covered by an acoustically active splice. The acoustically active splice includes a plurality of acoustic regions that provide for communication of noise energy to the noise attenuation layer to minimize creation of acoustically dead areas.

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