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    A COOLED GROMMET FOR A COMBUSTOR WALL ASSEMBLY
    1.
    发明申请
    A COOLED GROMMET FOR A COMBUSTOR WALL ASSEMBLY 审中-公开
    一个COOLUSTOR墙壁组件的冷却GROMMET

    公开(公告)号：WO2015147938A3

    公开(公告)日：2016-01-21

    申请号：PCT/US2014072358

    申请日：2014-12-24

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： SANDOVAL JONATHAN P

    IPC: F23M5/00 ,  F02C3/14 ,  F23M5/08 ,  F23R3/42

    CPC classification number: F23R3/045 ,  F02C3/14 ,  F05D2220/32 ,  F23R3/002 ,  F23R3/005 ,  F23R3/06 ,  F23R3/50 ,  F23R2900/03041 ,  F23R2900/03043 ,  Y02T50/675

    Abstract: A combustor wall assembly has a heat shield and a supporting shell with a cooling cavity defined therebetween. A grommet generally includes a wall defining a dilution hole isolated from the cooling cavity, and a flange projecting radially outward from the wall and into the cooling cavity. The flange is space from the heat shield and a cooling channel is defined between the wall and the heat shield that communicates with the cavity for cooling the wall proximate to a combustion chamber.

    Abstract translation: 燃烧器壁组件具有隔热罩和支撑壳体，其间限定有冷却腔。 索环通常包括限定与冷却腔隔离的稀释孔的壁，以及从壁径向向外突出并进入冷却腔的凸缘。 凸缘是与隔热罩的空间，并且在壁和隔热罩之间限定了冷却通道，该隔热件与空腔连通，用于冷却靠近燃烧室的壁。

    GAS TURBINE ENGINE ROTOR DISK-SEAL ARRANGEMENT
    3.
    发明公开
    GAS TURBINE ENGINE ROTOR DISK-SEAL ARRANGEMENT 有权
    用于燃气轮机电动机转子的盘座组件

    公开(公告)号：EP2971693A4

    公开(公告)日：2016-04-20

    申请号：EP14767917

    申请日：2014-03-14

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： PARTYKA JULIAN ,  SANDOVAL JONATHAN P

    IPC: F02C7/28 ,  F01D5/12 ,  F01D5/30 ,  F01D11/00 ,  F01D11/08

    CPC classification number: F01D11/001 ,  F01D5/027 ,  F01D5/3007 ,  F01D5/3015 ,  F02C7/28 ,  F05D2220/32 ,  F05D2240/12 ,  F05D2240/55 ,  F05D2250/73 ,  F05D2260/15 ,  Y02T50/673

    Abstract: A disk-seal arrangement for a gas turbine engine rotor includes a blade retention disk having a longitudinally opening slot therein and a seal disk juxtaposed to said blade retention disk and a single anti-rotation tab received within the blade retention disk slot. The seal disk also includes a pair of balance slots disposed immediately adjacent the antirotation tab to offset the weight thereof for preserving rotor balance. A split ring is disposed longitudinally between the blade retention and seal disks for reacting longitudinal loading therebetween. The ends of the split ring seat against side surfaces of the antirotation between the split ring and the blade retention and seal disks.

    Abstract translation: 用于燃气涡轮发动机转子的盘密封装置包括其中具有纵向开口槽的叶片保持盘和与所述刀片保持盘并置的密封盘和容纳在刀片保持盘槽内的单个防旋转突片。 密封盘还包括一对平衡槽，其紧邻防旋转翼片设置，以抵消其重量以保持转子平衡。 开口环纵向设置在叶片保持和密封盘之间，用于使它们之间的纵向载荷反应。 开口环座的端部抵靠开口环和叶片保持和密封盘之间的防旋转侧面。

    MULTI-STREAMED DILUTION HOLE CONFIGURATION FOR A GAS TURBINE ENGINE
    4.
    发明公开
    MULTI-STREAMED DILUTION HOLE CONFIGURATION FOR A GAS TURBINE ENGINE 审中-公开
    MEHRFACHDURCHSTRÖMTEVERDÜNNUNGSÖFFNUNGSKONFIGURATIONFÜREINEN GASTURBINENMOTOR

    公开(公告)号：EP3087266A4

    公开(公告)日：2017-05-17

    申请号：EP14874561

    申请日：2014-12-23

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： SANDOVAL JONATHAN P ,  SMITH RANDOLPH

    IPC: F02C7/12 ,  F23M5/08 ,  F23R3/42

    CPC classification number: F23R3/06 ,  F23R3/002 ,  F23R3/50 ,  F23R2900/03041 ,  Y02T50/675

    Abstract: A combustor component defining a dilution hole configuration for a combustor wall assembly of a gas turbine engine has first and second dilution holes that communicate radially with one-another and with respect to respective centerlines of each dilution hole. In operation, each dilution hole forms a respective jet stream along respective centerlines for flowing cooling air into a combustion chamber.

    Abstract translation: 限定用于燃气涡轮发动机的燃烧器壁组件的稀释孔配置的燃烧器部件具有第一和第二稀释孔，所述第一和第二稀释孔彼此径向地并且相对于每个稀释孔的相应中心线径向地连通。 在操作中，每个稀释孔沿相应的中心线形成相应的喷射流，用于使冷却空气流入燃烧室。

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