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    COOLING AN APERTURE BODY OF A COMBUSTOR WALL
    2.
    发明公开
    COOLING AN APERTURE BODY OF A COMBUSTOR WALL 审中-公开
    KÜHLUNGEINESÖFFNUNGSKÖRPERSEINER BRENNKAMMERWAND

    公开(公告)号：EP3084304A2

    公开(公告)日：2016-10-26

    申请号：EP14887292.2

    申请日：2014-12-19

    申请人： United Technologies Corporation

    发明人： KOSTKA, JR. Stanislav ,  CUNHA, Frank J.

    IPC分类号： F23M5/08 ,  F23R3/42 ,  F02C7/16

    CPC分类号： F23R3/005 ,  F02C7/12 ,  F23R3/06 ,  F23R2900/03042

    摘要： An assembly is provided for a turbine engine. This turbine engine assembly includes a combustor wall, which includes a shell, a heat shield and an annular body. The body at least partially defines a first aperture through the shell and the heat shield. The body also defines one or more second apertures through which air is directed into the first aperture and provides non-uniform cooling to the body.

    摘要翻译： 提供了一种用于涡轮发动机的组件。 该涡轮发动机组件包括燃烧器壁，其包括壳体，隔热罩和环形体。 主体至少部分地限定穿过外壳和隔热罩的第一孔。 身体还限定一个或多个第二孔，空气通过该孔被引导到第一孔中并且向身体提供不均匀的冷却。

    TURBINE ENGINE MULTI-WALLED STRUCTURE WITH COOLING ELEMENT(S)
    3.
    发明公开
    TURBINE ENGINE MULTI-WALLED STRUCTURE WITH COOLING ELEMENT(S) 审中-公开
    WITH冷却元件涡轮发动机的多壁结构（DE）

    公开(公告)号：EP3071887A1

    公开(公告)日：2016-09-28

    申请号：EP14864817.3

    申请日：2014-11-21

    申请人： United Technologies Corporation

    发明人： CUNHA, Frank J. ,  KOSTKA, JR., Stanislav

    IPC分类号： F23R3/42 ,  F23M5/08

    摘要： A multi-walled structure is provided for a turbine engine. This structure includes a shell with a textured first surface, and a heat shield with a second surface. The heat shield is attached to the shell. The first and the second surfaces vertically define a cooling cavity between the shell and the heat shield. The cooling cavity fluidly couples a plurality of cooling apertures defined in the shell with a plurality of cooling apertures defined in the heat shield.

    FUEL INJECTOR GUIDE(S) FOR A TURBINE ENGINE COMBUSTOR
    5.
    发明公开
    FUEL INJECTOR GUIDE(S) FOR A TURBINE ENGINE COMBUSTOR 审中-公开
    KRAFTSTOFFINJEKTORFÜHRUNG（EN）FÜREINE TURBINENBRENNKAMMER

    公开(公告)号：EP3032176A1

    公开(公告)日：2016-06-15

    申请号：EP15199626.1

    申请日：2015-12-11

    申请人： United Technologies Corporation

    发明人： CUNHA, Frank J. ,  KOSTKA, Stanislav

    IPC分类号： F23R3/10 ,  F23R3/28

    CPC分类号： F23R3/283 ,  F23R3/10 ,  F23R2900/03043 ,  F23R2900/03044 ,  F23R2900/03045

    摘要： A fuel injector (68) guide is provided for a turbine engine combustor 954). The fuel injector guide (68) includes a tubular base (86), an annular flange (88), a plurality of ribs (90, 92) and a flow turbulator (94). The base (86) extends along an axis (96) between first and second ends (98, 100). The flange (88) extends radially out from the base (86) at the second end (100). The ribs (90, 92) are disposed around the base (86) and extend axially out from the flange (88) towards the first end (98). The flow turbulator (94) is disposed between an adjacent pair of the ribs (90, 92).

    摘要翻译： 为涡轮发动机燃烧器954提供燃料喷射器（68）引导件。 燃料喷射器引导件（68）包括管状基座（86），环形凸缘（88），多个肋（90,92）和流动紊流器（94）。 基部（86）沿着第一和第二端（98,100）之间的轴线（96）延伸。 凸缘（88）在第二端（100）处从基座（86）径向向外延伸。 肋（90,92）围绕基部（86）设置并且从凸缘（88）朝向第一端（98）轴向地延伸。 流动湍流器（94）设置在相邻的一对肋（90,92）之间。

    NOZZLE GUIDE WITH INTERNAL COOLING FOR A GAS TURBINE ENGINE COMBUSTOR
    6.
    发明公开
    NOZZLE GUIDE WITH INTERNAL COOLING FOR A GAS TURBINE ENGINE COMBUSTOR 审中-公开
    具有内部冷却的燃气涡轮发动机的硝基JETS领导

    公开(公告)号：EP3026345A1

    公开(公告)日：2016-06-01

    申请号：EP15196098.6

    申请日：2015-11-24

    申请人： United Technologies Corporation

    发明人： CUNHA, Frank J. ,  KOSTKA, Stanislav

    IPC分类号： F23R3/28

    CPC分类号： F23R3/002 ,  F23R3/283 ,  F23R2900/03043 ,  F23R2900/03044

    摘要： A nozzle guide (105; 205; 300; 305; 405) is provided for a combustor (110) of a gas turbine engine (100). The nozzle guide includes an annular structure (130; 230; 330; 430) including a plurality of cooling holes (135; 235; 335; 435), a guide plate (140; 240; 340; 440) including a plurality of openings (145; 245; 345; 445) on an outer periphery of the guide plate, and a plurality of cooling passages (247; 334; 426) within the annular structure to provide air flow from the plurality of cooling holes to the plurality of openings.

    摘要翻译： 喷嘴引导（105; 205; 300; 305; 405）提供了一种用于燃气涡轮发动机（100）的燃烧器（110）。 喷嘴引导包括在环形结构（130; 230; 330; 430）包括冷却孔的多个（135; 235; 335; 435），导向板（140; 240; 340; 440）包括开口的多个（ 145; 245; 345; 445）上，在所述导向板的外周，冷却通道（247的多元性; 334;环形设计结构内426）以提供来自冷却孔以开口的多个的多个空气流。

    COMBUSTOR WALL APERATURE BODY WITH COOLING CIRCUIT
    7.
    发明公开
    COMBUSTOR WALL APERATURE BODY WITH COOLING CIRCUIT 有权
    BRENNKAMMERWANDÖFFNUNGSKÖRPERMITKÜHLKREISLAUF

    公开(公告)号：EP3018418A1

    公开(公告)日：2016-05-11

    申请号：EP15193737.2

    申请日：2015-11-09

    申请人： United Technologies Corporation

    发明人： CUNHA, Frank J. ,  KOSTKA, Stanislav

    IPC分类号： F23R3/06 ,  F23R3/04 ,  F23R3/50

    CPC分类号： F23R3/04 ,  F16C29/02 ,  F16C2360/23 ,  F23R3/002 ,  F23R3/045 ,  F23R3/06 ,  F23R3/50 ,  F23R2900/03044 ,  F23R2900/03045

    摘要： An assembly for a turbine engine 20 is provided that includes a combustor wall 76, 78, which includes an aperture body 100 between a shell 86, 88 and a heat shield 82, 84. The aperture body 100 at least partially forms a cavity 132 and an aperture 72, 74 that extends through the combustor wall 76, 78. An inlet passage 134 extends in the combustor wall 76, 78 to the cavity 132. An outlet passage 136 extends in the combustor wall 76, 78 from the cavity 132 to the aperture 72, 74.

    摘要翻译： 提供了一种用于涡轮发动机20的组件，其包括燃烧器壁76,78，燃烧器壁76,78包括壳体86,88和隔热罩82,84之间的孔体100.孔体100至少部分地形成空腔132和 延伸穿过燃烧器壁76,78的孔72,74。入口通道134在燃烧器壁76,78中延伸到空腔132.出口通道136在燃烧器壁76,78中从空腔132延伸到 孔72,74。