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    COOLING HOLE WITH ASYMMETRIC DIFFUSER
    1.
    发明申请
    COOLING HOLE WITH ASYMMETRIC DIFFUSER 审中-公开
    冷却孔与不对称扩散器

    公开(公告)号：WO2013165507A3

    公开(公告)日：2014-01-16

    申请号：PCT/US2013025705

    申请日：2013-02-12

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： GLEINER MATTHEW S ,  KOHLI ATUL ,  ZELESKY MARK F

    IPC: F02C7/18 ,  F01D5/08 ,  F01D25/12 ,  F02K3/00

    CPC classification number: F01D5/186 ,  F01D9/065 ,  F05D2240/81 ,  F05D2250/324 ,  F05D2250/73 ,  F05D2260/202 ,  F23R3/002 ,  F23R3/06 ,  F23R2900/00018 ,  F23R2900/03042 ,  Y02T50/676 ,  Y10T29/49323

    Abstract: A gas turbine engine component includes a wall having first and second wall surfaces and a cooling hole extending through the wall. The cooling hole includes an inlet located at the first wall surface, an outlet located at the second wall surface, a metering section extending downstream from the inlet and a diffusing section extending from the metering section to the outlet. The diffusing section includes a first lobe diverging longitudinally from the metering section and a second lobe adjacent the first lobe and diverging longitudinally and laterally from the metering section.

    Abstract translation: 燃气涡轮发动机部件包括具有第一和第二壁表面的壁和延伸穿过壁的冷却孔。 冷却孔包括位于第一壁表面的入口，位于第二壁表面处的出口，从入口下游延伸的计量部分和从计量部分延伸到出口的扩散部分。 漫射部分包括从计量部分纵向分散的第一凸角和邻近第一凸角的第二凸角并且从计量部分纵向和横向发散。

    COOLING HOLE WITH THERMO-MECHANICAL FATIGUE RESISTANCE
    2.
    发明申请
    COOLING HOLE WITH THERMO-MECHANICAL FATIGUE RESISTANCE 审中-公开
    具有热机械疲劳电阻的冷却孔

    公开(公告)号：WO2013165502A3

    公开(公告)日：2014-01-03

    申请号：PCT/US2013025680

    申请日：2013-02-12

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： KOHLI ATUL ,  GLEINER MATTHEW S ,  ZELESKY MARK F ,  XU JINQUAN

    IPC: F02C7/18 ,  F01D5/08 ,  F01D25/12 ,  F02K3/00

    CPC classification number: F23R3/06 ,  F01D5/186 ,  F01D9/065 ,  F05D2240/81 ,  F05D2260/202 ,  F23R2900/03042 ,  Y02T50/676

    Abstract: A gas turbine engine includes a wall having first and second wall surfaces and a cooling hole extending through the wall. The cooling hole includes an inlet located at the first wall surface, an outlet located at the second wall surface, a metering section extending downstream from the inlet and a diffusing section extending from the metering section to the outlet. The diffusing section includes a first lobe diverging longitudinally and laterally from the metering section, a second lobe diverging longitudinally and laterally from the metering section, an upstream end located at the outlet, a trailing edge located at the outlet opposite the upstream end and generally opposite first and second sidewalls. Each sidewall has an edge extending along the outlet between the upstream end and the trailing edge. Each edge diverges laterally from the upstream end and converges laterally before reaching the trailing edge.

    Abstract translation: 燃气涡轮发动机包括具有第一和第二壁表面的壁和延伸穿过壁的冷却孔。 冷却孔包括位于第一壁表面的入口，位于第二壁表面处的出口，从入口下游延伸的计量部分和从计量部分延伸到出口的扩散部分。 扩散部分包括从计量部分纵向和横向分叉的第一凸角，从计量部分纵向和横向分开的第二凸角，位于出口处的上游端，位于与上游端相对的出口处的后缘， 第一和第二侧壁。 每个侧壁具有沿着上游端和后缘之间的出口延伸的边缘。 每个边缘从上游端横向分开，并在到达后缘之前横向会聚。

    MULTI-LOBED COOLING HOLE AND METHOD OF MANUFACTURE
    3.
    发明申请
    MULTI-LOBED COOLING HOLE AND METHOD OF MANUFACTURE 审中-公开
    多孔冷却孔及其制造方法

    公开(公告)号：WO2013165510A3

    公开(公告)日：2014-01-09

    申请号：PCT/US2013025715

    申请日：2013-02-12

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： XU JINQUAN ,  ZELESKY MARK F ,  KOHLI ATUL ,  GLEINER MATTHEW S

    IPC: F02C7/18 ,  F01D5/08 ,  F01D25/12 ,  F02K3/00

    CPC classification number: F01D5/186 ,  F01D9/065 ,  F05D2240/81 ,  F05D2260/202 ,  Y02T50/676 ,  Y10T29/49323

    Abstract: A gas turbine engine component includes a wall having first and second wall surfaces and a cooling hole extending through the wall. The cooling hole includes an inlet at the first wall surface, an outlet at the second wall surface, a metering section extending downstream from the inlet and a diffusing section extending from the metering section to the outlet. The diffusing section includes a first lobe diverging longitudinally and laterally from the metering section, a second lobe adjacent the first lobe and diverging longitudinally from the metering section, a third lobe adjacent the second lobe and diverging longitudinally and laterally from the metering section, and a transition region having an end adjacent the outlet and a portion that extends between the lobes and the outlet. The first and third lobes each include a curved outer portion.

    Abstract translation: 燃气涡轮发动机部件包括具有第一和第二壁表面的壁和延伸穿过壁的冷却孔。 冷却孔包括在第一壁表面处的入口，在第二壁表面处的出口，从入口下游延伸的计量部分和从计量部分延伸到出口的扩散部分。 扩散部分包括从计量部分纵向和横向分散的第一凸角，与第一凸角相邻并且从计量部分纵向发散的第二凸角，邻近第二凸角并从计量部分纵向和横向发散的第三凸角，以及 过渡区域具有邻近出口的端部和在凸角和出口之间延伸的部分。 第一和第三瓣每个包括弯曲的外部部分。

    ROTOR BLADE WITH ONE OR MORE SIDE WALL MICROCOOLING CIRCUITS
    4.
    发明申请
    ROTOR BLADE WITH ONE OR MORE SIDE WALL MICROCOOLING CIRCUITS 审中-公开
    具有一个或多个侧壁微型电路的转子叶片

    公开(公告)号：WO2013154621A3

    公开(公告)日：2013-12-27

    申请号：PCT/US2013020845

    申请日：2013-01-09

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： DEVORE MATTHEW A ,  GLEINER MATTHEW S

    IPC: F01D5/18

    CPC classification number: F01D5/186 ,  F01D5/187 ,  F01D5/20 ,  F05D2240/307 ,  F05D2260/204

    Abstract: A rotor blade (26) for a gas turbine engine (10) includes an airfoil (34) and a cooling microcircuit (36, 38, 40). The airfoil (34) includes a first side wall (42), a second side wall (44) and a tip endwall (50), where the first side wall (42) and the second side wall (44) extend to and cooperate to form the tip endwall (50), defining a main cavity (62) between the first side wall (42) and the second side wall (44). The cooling microcircuit (36, 38, 40) includes a microcircuit cavity (72), an inlet (74), a side wall outlet (76) and a tip outlet (78). The microcircuit cavity (72) is embedded within the first side wall (72), and the inlet (74) extends from the main cavity (62) to the microcircuit cavity (72). The side wall outlet (76) extends from the microcircuit cavity (72) to an exterior first side surface of the airfoil (42). The tip outlet (78) extends from the microcircuit cavity (72) to an exterior tip surface (52, 54) of the airfoil.

    Abstract translation: 用于燃气涡轮发动机（10）的转子叶片（26）包括翼型件（34）和冷却微型电路（36,38,40）。 机翼（34）包括第一侧壁（42），第二侧壁（44）和末端壁（50），其中第一侧壁（42）和第二侧壁（44）延伸到并协作 形成尖端端壁（50），在第一侧壁（42）和第二侧壁（44）之间限定主空腔（62）。 冷却微电路（36,38,40）包括微电路腔（72），入口（74），侧壁出口（76）和尖端出口（78）。 微电路空腔（72）嵌入在第一侧壁（72）内，入口（74）从主腔（62）延伸到微电路腔（72）。 侧壁出口（76）从微电路空腔（72）延伸到翼型件（42）的外部第一侧表面。 尖端出口（78）从微型电路腔（72）延伸到翼型件的外部末端表面（52,54）。

    MULTI-LOBED COOLING HOLE
    5.
    发明申请
    MULTI-LOBED COOLING HOLE 审中-公开
    多出口冷却孔

    公开(公告)号：WO2013165509A2

    公开(公告)日：2013-11-07

    申请号：PCT/US2013025711

    申请日：2013-02-12

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： KOHLI ATUL ,  GLEINER MATTHEW S

    IPC: F02C7/18 ,  F01D5/08 ,  F01D25/12 ,  F02K3/00

    CPC classification number: F01D5/18 ,  F01D5/186 ,  F01D5/187 ,  F01D9/065 ,  F05D2240/81 ,  F05D2250/73 ,  F05D2260/202 ,  F23R3/002 ,  F23R3/06 ,  F23R2900/03042 ,  Y02T50/676

    Abstract: A gas turbine engine component subjected to a flow of high temperature gas includes a wall having first and second wall surfaces and a cooling hole extending through the wall. The cooling hole includes an inlet located at the first wall surface, an outlet located at the second wall surface, a metering section extending downstream from the inlet and a diffusing section extending from the metering section to the outlet. The diffusing section includes a first lobe, a second lobe and a transition region. The first lobe diverges longitudinally and laterally from the metering section and has a first shape. The second lobe is generally opposite the first lobe and diverges longitudinally and laterally from the metering section and has a second shape different from the first shape. The transition region is positioned between the first and second lobes and includes a downstream end adjacent the outlet.

    Abstract translation: 经受高温气体流动的燃气涡轮发动机部件包括具有第一和第二壁表面以及延伸穿过该壁的冷却孔的壁。 冷却孔包括位于第一壁表面处的入口，位于第二壁表面处的出口，从入口向下游延伸的计量部分以及从计量部分延伸至出口的扩散部分。 扩散部分包括第一叶片，第二叶片和过渡区域。 第一叶从计量部分纵向和横向分叉并具有第一形状。 第二叶片大体上与第一叶片相对并且从计量部分纵向和横向分叉并且具有不同于第一形状的第二形状。 过渡区位于第一和第二叶片之间并包括邻近出口的下游端。

    COOLING HOLE WITH THERMO-MECHANICAL FATIGUE RESISTANCE
    6.
    发明公开
    COOLING HOLE WITH THERMO-MECHANICAL FATIGUE RESISTANCE 审中-公开
    散热孔与抗病性的热机械疲劳

    公开(公告)号：EP2815103A4

    公开(公告)日：2016-01-06

    申请号：EP13784334

    申请日：2013-02-12

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： KOHLI ATUL ,  GLEINER MATTHEW S ,  ZELESKY MARK F ,  XU JINQUAN

    IPC: F01D9/06 ,  F01D5/18 ,  F23R3/00 ,  F23R3/06

    CPC classification number: F23R3/06 ,  F01D5/186 ,  F01D9/065 ,  F05D2240/81 ,  F05D2260/202 ,  F23R2900/03042 ,  Y02T50/676

    Abstract: A gas turbine engine includes a wall having first and second wall surfaces and a cooling hole extending through the wall. The cooling hole includes an inlet located at the first wall surface, an outlet located at the second wall surface, a metering section extending downstream from the inlet and a diffusing section extending from the metering section to the outlet. The diffusing section includes a first lobe diverging longitudinally and laterally from the metering section, a second lobe diverging longitudinally and laterally from the metering section, an upstream end located at the outlet, a trailing edge located at the outlet opposite the upstream end and generally opposite first and second sidewalls. Each sidewall has an edge extending along the outlet between the upstream end and the trailing edge. Each edge diverges laterally from the upstream end and converges laterally before reaching the trailing edge.

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