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    MOUNTING APPARATUS FOR A TRAILING EDGE BOX OF A GAS TURBINE AUGMENTOR
    1.
    发明申请
    MOUNTING APPARATUS FOR A TRAILING EDGE BOX OF A GAS TURBINE AUGMENTOR 审中-公开
    燃气涡轮增压装置的边坡装置安装装置

    公开(公告)号：WO2013106119A3

    公开(公告)日：2013-10-10

    申请号：PCT/US2012060220

    申请日：2012-10-15

    Applicant: UNITED TECHNOLOGIES CORP ,  WONG JOEY ,  LOFFREDO CONSTANTINO V ,  GRANT FERNANDO K

    Inventor： WONG JOEY ,  LOFFREDO CONSTANTINO V ,  GRANT FERNANDO K

    IPC: F02K3/10 ,  F23R3/28

    CPC classification number: B64D27/26 ,  B64D27/00 ,  B64D27/16 ,  B64D2027/262 ,  B64D2027/268 ,  F02K3/10 ,  F05D2240/91 ,  F05D2250/312 ,  F05D2260/30 ,  F23R3/20 ,  F23R3/283

    Abstract: A flanged apparatus includes an apparatus body and a flanged mount, which includes a support pylon, a first mounting flange and a second mounting flange. The support pylon includes a first pylon segment, a second pylon segment and a routing notch. The first pylon segment is cantilevered from the apparatus body, and extends to the first mounting flange. The second pylon segment is cantilevered from the first pylon support, and extends from the first mounting flange to the second mounting flange. The routing notch extends vertically between the first pylon segment and the second pylon segment. The first mounting flange and the second mounting flange extend laterally from the support pylon, and the first mounting flange is separated from the second mounting flange by a longitudinal distance and a vertical distance.

    Abstract translation: 一种带凸缘的装置包括装置主体和带凸缘的安装件，其包括支撑塔，第一安装凸缘和第二安装凸缘。 支撑塔包括第一吊架段，第二吊架段和路线槽。 第一个吊架段从装置主体悬臂，并延伸到第一安装法兰。 第二个吊架段从第一个支架支撑悬臂，并从第一安装法兰延伸到第二安装法兰。 导向槽在第一吊架段和第二吊架段之间垂直延伸。 第一安装凸缘和第二安装凸缘从支撑塔横向延伸，并且第一安装凸缘与第二安装凸缘分离，纵向距离和垂直距离。

    COMBUSTOR SEAL MISTAKE-PROOFING FOR A GAS TURBINE ENGINE
    2.
    发明申请
    COMBUSTOR SEAL MISTAKE-PROOFING FOR A GAS TURBINE ENGINE 审中-公开
    燃气轮机发动机油封密封失误检测

    公开(公告)号：WO2014099097A3

    公开(公告)日：2014-09-12

    申请号：PCT/US2013062874

    申请日：2013-10-01

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： LOW KEVIN JOSEPH ,  WONG JOEY

    IPC: F02C7/28 ,  F01D11/02 ,  F02C7/20

    CPC classification number: F02C7/28 ,  F01D9/023 ,  F01D11/00 ,  F01D11/003 ,  F02C3/04 ,  F23R2900/00012 ,  Y10T29/4932

    Abstract: A combustor seal for use between a downstream end of a combustor and a turbine vane includes a seal body and a plurality of seal alignment features. The plurality of seal alignment features projects from the seal body. The seal alignment features are arranged such that there is only one alignment of the combustor seal with the turbine vane.

    Abstract translation: 在燃烧器的下游端和涡轮叶片之间使用的燃烧器密封件包括密封体和多个密封对准特征。 多个密封对准特征从密封体突出。 密封对准特征被布置成使得燃烧器密封件与涡轮叶片只有一个对准。

    Annular combustor
    4.
    发明专利
    Annular combustor 未知

    公开(公告)号：GB2518750A

    公开(公告)日：2015-04-01

    申请号：GB201415057

    申请日：2013-01-14

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： EASTWOOD JONATHAN JEFFERY ,  WONG JOEY ,  SONNTAG ROBERT M

    IPC: F23R3/00 ,  F23R3/50 ,  F23R3/60

    Abstract: An annular combustor includes an annular outer shell that includes a first flange that defines an inner diameter IDOS and an annular inner shell that includes a second flange that defines an outer diameter ODIS. An annular hood includes a radially outer hood flange and a radially inner hood flange. A bulkhead includes a radially outer bulkhead flange that defines an outer diameter ODB and a radially inner bulkhead flange that defines an inner diameter IDB. The first flange is secured at a radially outer joint between the radially outer hood flange and the radially outer bulkhead flange. The second flange is secured at a radially inner joint between the radially inner hood flange and the radially inner bulkhead flange. The IDOS and the ODB define a ratio R1 of IDOS/ODB that is 0.998622-1.001129, and the IDB and the ODIS define a ratio R2 of IDB/ODIS that is 0.998812-1.001388.

    AXIAL TENSION SYSTEM FOR A GAS TURBINE ENGINE CASE
    7.
    发明公开
    AXIAL TENSION SYSTEM FOR A GAS TURBINE ENGINE CASE 审中-公开
    EINGEHÄUSEEINER GASTURBINE的AXIALSPANNUNGSSYSTEM

    公开(公告)号：EP2938843A4

    公开(公告)日：2016-03-23

    申请号：EP13869591

    申请日：2013-12-27

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： WONG JOEY ,  ZHENG ZHIJUN

    IPC: F01D25/24 ,  F01D25/00 ,  F02C7/00

    CPC classification number: F02C7/20 ,  F01D25/162 ,  F01D25/24 ,  F05D2250/711 ,  F05D2260/30

    Abstract: A gas turbine engine includes a convex case section. The convex case section includes an upstream case portion having a first radius, a downstream case portion having a second radius, and an intermediate case portion between the upstream case portion and the downstream case portion. The intermediate case portion has a third radius larger than the first radius and the second radius. A tension rod extends from the upstream case portion to the downstream case portion.

    Abstract translation: 燃气涡轮发动机包括凸壳部分。 凸形壳体部分包括具有第一半径的上游壳体部分，具有第二半径的下游壳体部分，以及在上游壳体部分和下游壳体部分之间的中间壳体部分。 中间壳体部分具有大于第一半径和第二半径的第三半径。 张力杆从上游壳体部分延伸到下游壳体部分。

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