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    GAS TURBINE ENGINE RAPID RESPONSE CLEARANCE CONTROL SYSTEM WITH VARIABLE VOLUME TURBINE CASE
    3.
    发明申请
    GAS TURBINE ENGINE RAPID RESPONSE CLEARANCE CONTROL SYSTEM WITH VARIABLE VOLUME TURBINE CASE 审中-公开
    气体涡轮发动机快速响应间隙控制系统与可变容积涡轮机箱

    公开(公告)号：WO2014186003A3

    公开(公告)日：2015-02-26

    申请号：PCT/US2014015080

    申请日：2014-02-06

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： BLANEY KEN F ,  LAPIERRE TODD M

    IPC: F01D11/20 ,  F01D11/22 ,  F02C7/28 ,  F04D29/08

    CPC classification number: F01D11/22 ,  F01D25/24 ,  F02C7/28 ,  F05D2220/32 ,  F05D2240/55 ,  F05D2260/42 ,  F05D2270/60

    Abstract: An active clearance control system of a gas turbine engine includes a radially adjustable blade outer air seal system movable between a radially contracted Blade Outer Air Seal (BOAS) position that defines a first air volume and a radially expanded Blade Outer Air Seal (BOAS) position that defines a second air volume, the second air volume different than the first air volume. An accumulator system accommodate a difference in air volume between the first air volume and the second air volume.

    Abstract translation: 燃气涡轮发动机的主动间隙控制系统包括可径向调节的叶片外部空气密封系统，其可在限定第一空气体积的径向收缩的叶片外部空气密封（BOAS）位置和径向扩展的叶片外部空气密封（BOAS）位置之间移动 其限定第二风量，第二风量与第一风量不同。 蓄能器系统适应第一风量和第二风量之间的空气量的差异。

    BLADE OUTER AIR SEAL FIN COOLING ASSEMBLY AND METHOD
    4.
    发明申请
    BLADE OUTER AIR SEAL FIN COOLING ASSEMBLY AND METHOD 审中-公开
    叶片外部密封件冷却组件和方法

    公开(公告)号：WO2015175042A3

    公开(公告)日：2016-01-14

    申请号：PCT/US2015015540

    申请日：2015-02-12

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： ROMANOV DMITRIY A ,  PAULINO JOSE R ,  BLANEY KEN F

    IPC: F01D11/08 ,  F01D25/12 ,  F02C7/18 ,  F02C7/28

    CPC classification number: F01D11/08 ,  B22C9/10 ,  B22C9/24 ,  F01D11/24 ,  F05D2230/211 ,  F05D2240/11 ,  F05D2260/204 ,  F05D2260/22141 ,  F05D2300/13 ,  Y02T50/676

    Abstract: A blade outer air seal according to an exemplary aspect of the present disclosure includes, among other things, a body to be distributed circumferentially about a blade array. The body has a plurality of grooves, which can, for example, improve the aerodynamic efficiency of a turbine. A fin is between a first groove and a second groove of the plurality of grooves. The fin extends radially from the body and terminates at a radially inner fin face that provides one or more cooling outlets.

    Abstract translation: 根据本公开的示例性方面的叶片外部空气密封件尤其包括围绕叶片阵列周向分布的主体。 主体具有多个凹槽，其可以例如改善涡轮机的空气动力学效率。 翅片在多个凹槽的第一凹槽和第二凹槽之间。 翅片从主体径向延伸并且终止于提供一个或多个冷却出口的径向内部翅片面。

    ACCESSIBLE RAPID RESPONSE CLEARANCE CONTROL SYSTEM
    6.
    发明申请
    ACCESSIBLE RAPID RESPONSE CLEARANCE CONTROL SYSTEM 审中-公开
    可接近的快速响应间隙控制系统

    公开(公告)号：WO2015102949A3

    公开(公告)日：2015-09-11

    申请号：PCT/US2014071503

    申请日：2014-12-19

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： BLANEY KEN F ,  HAYFORD RICHARD K ,  JAROCHYM CHRISTOPHER M

    IPC: F01D11/22

    CPC classification number: F01D11/20 ,  F01D5/12 ,  F01D11/22 ,  F01D25/24 ,  F05D2240/11 ,  F05D2270/64 ,  F05D2270/65

    Abstract: An example active clearance control system for a gas turbine engine includes an actuator, and a case wall portion defining an aperture configured to receive the actuator. The actuator is configured to move an air seal segment, and the actuator is insertable to an installed position within the aperture through a radially outer side of the case wall portion.

    Abstract translation: 用于燃气涡轮发动机的示例主动间隙控制系统包括致动器和限定配置成接收致动器的孔的壳体壁部分。 致动器构造成移动气密段，并且致动器可通过壳体壁部分的径向外侧插入孔内的安装位置。

    ACTIVE CLEARANCE CONTROL SYSTEM WITH ZONE CONTROLS
    8.
    发明申请
    ACTIVE CLEARANCE CONTROL SYSTEM WITH ZONE CONTROLS 审中-公开
    带有区域控制的主动间隙控制系统

    公开(公告)号：WO2014116325A2

    公开(公告)日：2014-07-31

    申请号：PCT/US2013068672

    申请日：2013-11-06

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： BLANEY KEN F ,  LUTJEN PAUL M

    CPC classification number: F01D11/24

    Abstract: An ACC system and method of using such for changing a turbine blade to BOAS gap on an aircraft engine is disclosed. The ACC system may comprise a first ring, a first supply line and a first flow control assembly. The first ring may be configured to substantially encircle a portion of a case assembly that is disposed around an aircraft engine turbine. The first ring may include a plurality of segments that each define a chamber, an inlet port and a plurality of outlet ports. At least a portion of the outlet ports may be configured to be disposed adjacent to the case. The first supply line may be operatively connected to a first segment of the plurality of segments. The first flow control assembly may be operatively connected to the first supply line and configured to meter the flow of cool air into the first segment.

    Abstract translation: 公开了一种ACC系统及其用于将涡轮叶片更换为飞机发动机上的BOAS间隙的方法。 ACC系统可以包括第一环，第一供应管线和第一流量控制组件。 第一环可以构造成基本上环绕设置在飞机发动机涡轮周围的壳体组件的一部分。 第一环可以包括多个分段，每个分段限定腔室，入口端口和多个出口端口。 出口端口的至少一部分可以被配置为邻近壳体设置。 第一供应管线可操作地连接到多个节段的第一节段。 第一流量控制组件可以可操作地连接到第一供应管线并且被配置成计量冷空气流入第一分段。

    CANTED BOAS INTERSEGMENT GEOMETRY
    9.
    发明公开
    CANTED BOAS INTERSEGMENT GEOMETRY 审中-公开
    GENEIGTE BOAS-INTERSEGMENT-GEOMETRIE

    公开(公告)号：EP3042045A4

    公开(公告)日：2017-06-14

    申请号：EP14842420

    申请日：2014-08-25

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： BLANEY KEN F

    IPC: F01D11/08 ,  F01D11/14 ,  F02C7/28 ,  F04D29/08

    CPC classification number: F01D25/12 ,  F01D5/02 ,  F01D5/12 ,  F01D11/08 ,  F01D11/10 ,  F01D11/18 ,  F01D11/24 ,  F05D2220/32 ,  F05D2240/55 ,  F05D2260/20

    Abstract: A blade outer air seal segment has an inner surface and an outer surface. The outer surface is in communication with a cooling air source. The segment also has a first end having a first surface extending from the inner surface and a first angled surface extending from the first surface, and a second end having a second surface extending from the inner surface and a second angled surface extending from the second surface.

    Abstract translation: 叶片外部空气密封段具有内表面和外表面。 外表面与冷却空气源连通。 该段还具有第一端和第二端，第一端具有从内表面延伸的第一表面和从第一表面延伸的第一倾斜表面，第二端具有从内表面延伸的第二表面和从第二表面延伸的第二倾斜表面 。

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