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    SELF CRYSTALLINE ORIENTATION FOR INCREASED COMPLIANCE
    16.
    发明申请
    SELF CRYSTALLINE ORIENTATION FOR INCREASED COMPLIANCE 审中-公开
    自主研发的方向提高了符合性

    公开(公告)号：US20170044918A1

    公开(公告)日：2017-02-16

    申请号：US14825812

    申请日：2015-08-13

    Applicant: United Technologies Corporation

    Inventor： Michael G. McCaffrey ,  Eric A. Hudson

    IPC: F01D11/02 ,  F16J15/44

    CPC classification number: F01D11/02 ,  F01D5/16 ,  F01D5/22 ,  F01D5/24 ,  F01D11/006 ,  F01D11/16 ,  F02C7/28 ,  F05D2220/323 ,  F05D2240/55 ,  F05D2250/71 ,  F05D2300/17 ,  F05D2300/607 ,  F16J15/44

    Abstract: Aspects of the disclosure are directed to a seal comprising: a shoe, and at least one beam coupled to the shoe, wherein the seal includes a single crystal material with a predetermined crystalline orientation. Aspects of the disclosure are directed to a method for designing a seal, comprising: obtaining a requirement associated with at least one of: a geometrical profile of the seal, a temperature range over which the seal is to operate, a natural frequency associated with the seal, or a range of deflection associated with the seal, selecting a crystalline orientation for a single crystal material of the seal based on the requirement, and fabricating the seal based on the selected crystalline orientation.

    Abstract translation: 本公开的方面涉及一种密封件，其包括：鞋，以及耦合到鞋的至少一个梁，其中所述密封件包括具有预定结晶取向的单晶材料。 本公开的方面涉及一种用于设计密封件的方法，包括：获得与以下中的至少一个相关联的要求：密封件的几何轮廓，密封件将在其上操作的温度范围，与 密封或与密封件相关的一系列偏转，基于要求为密封件的单晶材料选择晶体取向，以及基于所选择的晶体取向制造密封件。

    Thermal lifting member for blade outer air seal support
    18.
    发明授权
    Thermal lifting member for blade outer air seal support 有权

    公开(公告)号：US10415420B2

    公开(公告)日：2019-09-17

    申请号：US15093972

    申请日：2016-04-08

    Applicant: United Technologies Corporation

    Inventor： David J. Wasserman ,  Scott D. Virkler ,  Eric A. Hudson ,  Ryan W. Brandt

    IPC: F01D11/24 ,  F01D5/12 ,  F01D25/24 ,  F01D11/14 ,  F01D11/18

    Abstract: Thermal lifting members for blade outer air seal supports of gas turbine engines include a hollow body defining a thermal cavity therein, at least one inlet fluid connector fluidly connected to the thermal cavity configured to supply hot fluid to the thermal cavity from a fluid source, at least one outlet fluid connector fluidly connected to the thermal cavity configured to allow the hot fluid to exit the thermal cavity, and at least one lifting hook configured to engage with a blade outer air seal support, wherein the thermal lifting member is configured to thermally expand outward when hot fluid is passed through the thermal cavity such that during thermal expansion the at least one lifting hook forces the blade outer air seal support to move outward.

    Airfoil cooling circuits
    19.
    发明授权
    Airfoil cooling circuits 有权

    公开(公告)号：US10400609B2

    公开(公告)日：2019-09-03

    申请号：US15866134

    申请日：2018-01-09

    Applicant: United Technologies Corporation

    Inventor： Eric A. Hudson ,  Tracy A. Propheter-Hinckley ,  San Quach ,  Matthew A. Devore

    IPC: B22C9/10 ,  B22C9/24 ,  F01D5/18

    Abstract: An airfoil includes leading and trailing edges; first and second sides extending from the leading edge to the trailing edge, each side having an exterior surface; a core passage located between the first and second sides and the leading and trailing edges; and a wall structure located between the core passage and the exterior surface of the first side. The wall structure includes a plurality of cooling fluid inlets communicating with the core passage for receiving cooling fluid from the core passage, a plurality of cooling fluid outlets on the exterior surface of the first side for expelling cooling fluid and forming a cooling film along the exterior surface of the first side, and a plurality of cooling passages communicating with the plurality of cooling fluid inlets and the plurality of cooling fluid outlets. At least a portion of one cooling passage extends between adjacent cooling fluid outlets.

    Compact advanced passive tip clearance control
    20.
    发明授权
    Compact advanced passive tip clearance control 有权

    公开(公告)号：US10344612B2

    公开(公告)日：2019-07-09

    申请号：US15405778

    申请日：2017-01-13

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Eric A. Hudson ,  Michael G. McCaffrey ,  Stanley J. Funk ,  Scott D. Virkler

    IPC: F01D11/18 ,  F01D11/02 ,  F01D5/20 ,  F01D25/24 ,  F02C3/04 ,  F04D29/32 ,  F04D29/52 ,  F04D29/08 ,  F04D29/64

    Abstract: A section of a gas turbine engine includes a rotor blade designed to rotate about an axis. The section also includes a case positioned radially outward from the rotor blade and extending circumferentially about the axis. The section also includes a control ring being annular, positioned radially inward from the case and designed to move radially relative to the case. The section also includes a segmented blade outer air seal (BOAS) including a plurality of BOAS segments each being positioned radially outward from the rotor blade, movably coupled to the control ring, and designed to move circumferentially relative to each other such that a circumferential gap between each of the plurality of BOAS segments changes in size in response to a temperature change in the section of the gas turbine engine.

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