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    GAS TURBINE ENGINE AIRFOIL TURBULATOR FOR AIRFOIL CREEP RESISTANCE
    1.
    发明申请
    GAS TURBINE ENGINE AIRFOIL TURBULATOR FOR AIRFOIL CREEP RESISTANCE 审中-公开
    气体涡轮发动机空气涡轮机涡轮机抗风性能

    公开(公告)号：WO2015073092A3

    公开(公告)日：2015-08-06

    申请号：PCT/US2014052850

    申请日：2014-08-27

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： THISTLE CHARLES ,  THORNTON LANE

    IPC: F01D5/18

    CPC classification number: F01D5/187 ,  F05D2220/32 ,  F05D2240/304 ,  F05D2260/2212 ,  F05D2260/22141 ,  Y02T50/676

    Abstract: A gas turbine engine component includes spaced apart walls that extend in a load direction and provide a cooling passage. The cooling passage provides a tortuous passage having a generally straight portion that extends in the load direction and a bend transverse to the load direction. Elongated turbulators protrude from at least one of the walls and extend substantially in the load direction. The elongated turbulators are substantially within the generally straight portion.

    Abstract translation: 燃气涡轮发动机部件包括在负载方向上延伸并提供冷却通道的间隔开的壁。 冷却通道提供具有在负载方向上延伸的大致直的部分和横向于负载方向的弯曲的曲折通道。 细长的湍流器从至少一个壁突出并基本上在负载方向上延伸。 细长的湍流器基本上在大致直的部分内。

    CENTRIFUGAL AIRFOIL COOLING MODULATION
    2.
    发明申请
    CENTRIFUGAL AIRFOIL COOLING MODULATION 审中-公开
    离心式空气冷却调节

    公开(公告)号：WO2015112268A2

    公开(公告)日：2015-07-30

    申请号：PCT/US2014069128

    申请日：2014-12-08

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： THORNTON LANE ,  SLAVENS THOMAS N

    IPC: F01D5/18

    CPC classification number: F01D5/186 ,  F01D5/187 ,  F01D5/28 ,  F02C3/04 ,  F02C7/12 ,  F05D2220/32 ,  F05D2240/303 ,  F05D2240/304 ,  F05D2260/201 ,  F05D2260/202 ,  F05D2300/175 ,  F05D2300/505 ,  Y02T50/676

    Abstract: In one example embodiment, a blade includes an attachment region, an airfoil extending from the attachment region, and a blade cooling arrangement. The blade cooling arrangement includes at least a first feed passage disposed through the attachment region, which is connected to a first cooling passage disposed in the airfoil. A passively actuated first coolant valve is disposed in or proximate the first feed passage. A plurality of such blades can be disposed in a turbine section of an engine.

    Abstract translation: 在一个示例性实施例中，叶片包括附接区域，从连接区域延伸的翼型件和叶片冷却装置。 叶片冷却装置包括至少一个穿过安装区域设置的第一进料通道，其连接到设置在翼型件中的第一冷却通道。 被动地驱动的第一冷却剂阀设置在第一进料通道中或其附近。 多个这样的叶片可以设置在发动机的涡轮机部分中。

    FAN COOLING HOLE ARRAY
    3.
    发明申请
    FAN COOLING HOLE ARRAY 审中-公开
    风扇冷却孔阵列

    公开(公告)号：WO2015163949A2

    公开(公告)日：2015-10-29

    申请号：PCT/US2015010010

    申请日：2015-01-02

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： THORNTON LANE ,  DEVORE MATTHEW A ,  MONGILLO DOMINIC J ,  GAUTSCHI STEVEN BRUCE

    IPC: F01D5/18

    CPC classification number: F01D5/186 ,  F05D2220/32 ,  F05D2240/303 ,  F05D2250/14 ,  F05D2250/312 ,  F05D2250/313 ,  F05D2250/314 ,  F05D2250/324 ,  F05D2250/38 ,  F05D2260/202 ,  Y02T50/673 ,  Y02T50/676

    Abstract: A gas turbine engine component comprises an airfoil with a suction side and pressure side extending from a leading edge to a trailing edge. There are a plurality of cooling holes adjacent the leading edge, with the cooling holes having a non-circular shape, with a longer dimension and a smaller dimension. The airfoil defines a radial direction from a radially outer end to a radially inner end, and radially outer of the cooling holes spaced toward the radially outer end, which have the longer dimension extending closer to parallel to the radial direction. Radially inner cooling holes closer to the radially inner end having the longer dimension extend to be closer to perpendicular relative to the radial direction compared to the radially outer cooling holes.

    Abstract translation: 燃气涡轮发动机部件包括翼型，翼型具有从前缘延伸到后缘的吸入侧和压力侧。 在前缘附近有多个冷却孔，冷却孔具有非圆形形状，具有较长的尺寸和较小的尺寸。 翼型限定从径向外端到径向内端的径向方向，并且径向外部的朝向径向外端间隔开的冷却孔具有更接近平行于径向方向延伸的较长尺寸。 与径向外部冷却孔相比，更靠近具有较长尺寸的径向内端的径向内部冷却孔延伸到相对于径向方向更接近垂直。

    GAS TURBINE ENGINE COMPONENT WITH SEPARATION RIB FOR COOLING PASSAGES
    4.
    发明申请
    GAS TURBINE ENGINE COMPONENT WITH SEPARATION RIB FOR COOLING PASSAGES 审中-公开
    具有用于冷却通道的分离RIB的气体涡轮发动机部件

    公开(公告)号：WO2015160404A3

    公开(公告)日：2016-03-10

    申请号：PCT/US2015012119

    申请日：2015-01-21

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： THISTLE CHARLES ,  THORNTON LANE

    IPC: F02C7/16 ,  F01D5/18 ,  F01D25/12

    CPC classification number: F01D25/12 ,  F01D5/187 ,  F01D11/08 ,  F01D11/24 ,  F02C3/10 ,  F02C7/12 ,  F02K3/06 ,  F05D2240/11 ,  F05D2250/11 ,  F05D2250/121 ,  F05D2250/22 ,  F05D2250/23 ,  F05D2250/25 ,  F05D2260/2212 ,  F05D2260/2214 ,  Y02T50/676

    Abstract: A gas turbine engine component comprises a body extending between two ends and having at least two cooling passages. The body has a first wall and second wall. At least two cooling passages include a first passage that is closer to the first wall than is a second of the passages at upstream locations along a flow path. The second passage has upstream locations that are closer to the second wall than are upstream portions of the first passage. The first and second passages cross along a length of the flow path such that downstream portions of the second passage are closer to the first wall than are downstream portions of the first passage, and downstream portions of the first passage are closer to the second wall than are downstream portions of the second passage.

    Abstract translation: 燃气涡轮发动机部件包括在两端之间延伸并且具有至少两个冷却通道的主体。 身体有第一个墙壁和第二个墙壁。 至少两个冷却通道包括比沿着流动路径的上游位置处的第二通道更靠近第一壁的第一通道。 第二通道具有比第一通道的上游部分更靠近第二壁的上游位置。 所述第一通道和所述第二通道沿所述流动路径的长度交叉，使得所述第二通道的下游部分比所述第一通道的下游部分更靠近所述第一壁，并且所述第一通道的下游部分比所述第一通道的下游部分更靠近所述第二壁 是第二通道的下游部分。

    LOST CORE MOLDING CORES FOR FORMING COOLING PASSAGES
    7.
    发明公开
    LOST CORE MOLDING CORES FOR FORMING COOLING PASSAGES 审中-公开
    FORMUNG VON KERNEN ZUR HERSTELLUNG VONKÜHLKANÄLEN

    公开(公告)号：EP3060363A4

    公开(公告)日：2017-07-26

    申请号：EP14856477

    申请日：2014-09-26

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： THORNTON LANE ,  QUACH SAN ,  GAUTSCHI STEVEN BRUCE

    IPC: B22C9/04 ,  B22C7/02

    CPC classification number: B22C9/103

    Abstract: In a featured embodiment, a lost core assembly includes a ceramic component having a tapered shape in a radial direction. A refractory metal component extends radially from the ceramic core component. A method of molding a gas turbine engine component is also disclosed.

    Abstract translation: 在特征实施例中，迷路芯组件包括沿径向具有锥形形状的陶瓷部件。 难熔金属部件从陶瓷芯部件径向延伸。 还公开了一种模制燃气涡轮发动机部件的方法。

    GAS TURBINE ENGINE AIRFOIL TURBULATOR FOR AIRFOIL CREEP RESISTANCE
    8.
    发明公开
    GAS TURBINE ENGINE AIRFOIL TURBULATOR FOR AIRFOIL CREEP RESISTANCE 审中-公开
    燃气轮机发动机顶翼抗风雨

    公开(公告)号：EP3042041A4

    公开(公告)日：2016-09-28

    申请号：EP14862682

    申请日：2014-08-27

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： THISTLE CHARLES ,  THORNTON LANE

    IPC: F01D5/18

    CPC classification number: F01D5/187 ,  F05D2220/32 ,  F05D2240/304 ,  F05D2260/2212 ,  F05D2260/22141 ,  Y02T50/676

    Abstract: A gas turbine engine component includes spaced apart walls that extend in a load direction and provide a cooling passage. The cooling passage provides a tortuous passage having a generally straight portion that extends in the load direction and a bend transverse to the load direction. Elongated turbulators protrude from at least one of the walls and extend substantially in the load direction. The elongated turbulators are substantially within the generally straight portion.

    Abstract translation: 燃气涡轮发动机部件包括在负载方向上延伸并提供冷却通道的间隔开的壁。 冷却通道提供具有在负载方向上延伸的大致直线部分和横向于负载方向的弯曲部的曲折通道。 细长的湍流器从至少一个壁突出并基本上在负载方向上延伸。 细长的湍流器基本上在大致直的部分内。

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