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    NON-LINE OF SIGHT ELECTRO DISCHARGE MACHINED PART
    1.
    发明申请
    NON-LINE OF SIGHT ELECTRO DISCHARGE MACHINED PART 审中-公开
    非线性电子放电加工部分

    公开(公告)号：WO2014105393A1

    公开(公告)日：2014-07-03

    申请号：PCT/US2013/073618

    申请日：2013-12-06

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： KOONANKEIL, James M. ,  PIETRASZKIEWICZ, Edward F. ,  SCHACHTNER, Karl A. ,  KLINEFELTER, Kevin J. ,  FRITCH, Markus W. ,  DALEY, Jason

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

    CPC classification number: B23H1/00 ,  B23H7/265 ,  B23H7/30 ,  B23H9/10 ,  F01D5/187 ,  F05D2230/12 ,  F05D2240/12 ,  F05D2240/81 ,  Y02T50/676 ,  Y10T29/49323 ,  Y10T29/49341

    Abstract: A method of machining cooling holes in a component includes the steps of inserting an electro discharge machining guide that houses an electrode into an internal cavity of a component, and machining a cooling hole into a wall of the component with the electrode. A gas turbine engine component includes first and second spaced apart walls providing an internal cavity. The first wall has outer and inner surfaces. The inner surface faces the internal cavity. A cooling hole extends through the first wall from the inner surface to the outer surface. The cooling hole includes entry and exit openings respectively provided in the inner and outer surfaces. The exit opening includes a cross-sectional area that is smaller than a cross-sectional area of the entry opening.

    Abstract translation: 在部件中加工冷却孔的方法包括以下步骤：将容纳电极的放电加工引导件插入部件的内部空腔中，并用电极将冷却孔加工到部件的壁中。 燃气涡轮发动机部件包括提供内腔的第一和第二隔开的壁。 第一个墙壁有外表面和内表面。 内表面面向内腔。 冷却孔从内表面到外表面延伸穿过第一壁。 冷却孔包括分别设置在内表面和外表面上的入口和出口。 出口开口包括比入口开口的横截面面积小的横截面面积。

    INSPECTING ONE OR MORE APERTURES OF A COMPONENT USING MOLDABLE MATERIAL
    2.
    发明申请
    INSPECTING ONE OR MORE APERTURES OF A COMPONENT USING MOLDABLE MATERIAL 审中-公开
    使用可塑材料检查组件的一个或多个孔

    公开(公告)号：WO2014134057A1

    公开(公告)日：2014-09-04

    申请号：PCT/US2014/018370

    申请日：2014-02-25

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： REED, Gordon M. ,  ROMANELLI, James ,  KOONANKEIL, James M. ,  KLINEFELTER, Kevin J. ,  FRITCH, Markus W. ,  HOLLMAN, Kenneth J. ,  BEATTIE, Jeffrey S.

    IPC: G01B11/00 ,  G01M13/00

    CPC classification number: G01B11/00 ,  G01B11/24 ,  G01B21/20 ,  G01M13/00

    Abstract: A method is provided for inspecting at least one aperture of a component with curable material and an inspection system. At least a portion of the curable material is injected into the aperture. The curable material conforms to at least a portion the aperture and subsequently cures and forms a mold of at least a portion of the aperture. The mold is removed from the aperture. At least a portion of a geometry of the mold is compared to at least a portion of a geometry of a reference model for the aperture using the inspection system.

    Abstract translation: 提供了一种用于使用可固化材料和检查系统检查部件的至少一个孔的方法。 至少一部分可固化材料被注入孔中。 可固化材料符合孔的至少一部分并随后固化并形成孔的至少一部分的模具。 将模具从孔中取出。 将模具的几何形状的至少一部分与使用检查系统的孔的参考模型的几何形状的至少一部分进行比较。

    NON-LINE OF SIGHT ELECTRO DISCHARGE MACHINED PART
    4.
    发明公开
    NON-LINE OF SIGHT ELECTRO DISCHARGE MACHINED PART 审中-公开
    MITTELS DRAHTEROSION OHNE SICHTVERBINDUNG BEARBEITETES TEIL

    公开(公告)号：EP2971539A1

    公开(公告)日：2016-01-20

    申请号：EP13866646.6

    申请日：2013-12-06

    Applicant: United Technologies Corporation

    Inventor： KOONANKEIL, James M. ,  PIETRASZKIEWICZ, Edward F. ,  SCHACHTNER, Karl A. ,  KLINEFELTER, Kevin J. ,  FRITCH, Markus W. ,  DALEY, Jason

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

    Abstract: A method of machining cooling holes in a component includes the steps of inserting an electro discharge machining guide that houses an electrode into an internal cavity of a component, and machining a cooling hole into a wall of the component with the electrode. A gas turbine engine component includes first and second spaced apart walls providing an internal cavity. The first wall has outer and inner surfaces. The inner surface faces the internal cavity. A cooling hole extends through the first wall from the inner surface to the outer surface. The cooling hole includes entry and exit openings respectively provided in the inner and outer surfaces. The exit opening includes a cross-sectional area that is smaller than a cross-sectional area of the entry opening.

    Abstract translation: 一种在部件中加工冷却孔的方法包括以下步骤：将容纳电极的放电加工引导件插入部件的内部空腔中，并用电极将冷却孔加工到部件的壁中。 燃气涡轮发动机部件包括提供内腔的第一和第二隔开的壁。 第一个墙壁有外表面和内表面。 内表面面向内腔。 冷却孔从内表面到外表面延伸穿过第一壁。 冷却孔包括分别设置在内表面和外表面上的入口和出口。 出口开口包括小于入口的横截面积的横截面面积。

    AIRFOIL RESONANT FREQUENCY TESTING
    6.
    发明公开
    AIRFOIL RESONANT FREQUENCY TESTING 审中-公开
    TRAGFLÜGELRESONANZFREQUENZPRÜFUNG

    公开(公告)号：EP3056879A1

    公开(公告)日：2016-08-17

    申请号：EP16154817.7

    申请日：2016-02-09

    Applicant: United Technologies Corporation

    Inventor： TINE, Steven ,  LOMENZO, Richard A. ,  KLINEFELTER, Kevin J. ,  VINSON, Elizabeth F. ,  OLSEN, Kaitlin ,  DAVIS, Thomas R.

    IPC: G01H13/00

    CPC classification number: F01D21/003 ,  F05D2240/12 ,  F05D2240/30 ,  F05D2260/12 ,  G01H9/00 ,  G01H13/00

    Abstract: A resonant frequency testing system for airfoils 12 comprises a broach block 16, a clamp 18, an acoustic speaker 20, a laser vibrometer 22, and a control processor assembly 38. The broach block has a slot disposed to receive the airfoil in an airfoil location. The clamp 18 has a torque-actuated shutoff, and is disposed to lock the airfoil 12 in the broach block slot under a fixed clamping force. The acoustic speaker 20 is disposed adjacent the airfoil location to emit sonic pulses, and the laser vibrometer 22 is oriented towards the airfoil location to sense vibration signatures of the airfoil 12 when excited by the sonic pulses. The control processor assembly 38 is configured to control the acoustic speaker 20 and laser vibrometer 22, to decompose the sensed vibration signatures into resonant frequencies of the airfoil 12, and to store the resonant frequencies in a digital storage database, correlated with a unique ID corresponding to the airfoil.

    Abstract translation: 用于翼型件12的谐振频率测试系统包括拉刀块16，夹具18，声音扬声器20，激光振动计22和控制处理器组件38.拉刀块具有设置成在翼型位置中接收翼型的槽 。 夹具18具有转矩驱动关闭，并且被设置成在固定夹紧力下将翼型件12锁定在拉刀块槽中。 声音扬声器20邻近翼型位置设置以发射声波脉冲，并且激光振动计22朝向翼型位置定向以在由声波脉冲激发时感测到翼型12的振动特征。 控制处理器组件38被配置为控制声学扬声器20和激光振动计22，以将感测到的振动特征分解成翼型12的谐振频率，并将谐振频率存储在数字存储数据库中，与相应的唯一ID相关联 到机翼。

    AIRFOIL RESONANT FREQUENCY TESTING
    9.
    发明授权
    AIRFOIL RESONANT FREQUENCY TESTING 有权

    公开(公告)号：EP3056879B1

    公开(公告)日：2018-11-14

    申请号：EP16154817.7

    申请日：2016-02-09

    Applicant: United Technologies Corporation

    Inventor： TINE, Steven ,  LOMENZO, Richard A. ,  KLINEFELTER, Kevin J. ,  VINSON, Elizabeth F. ,  OLSEN, Kaitlin ,  DAVIS, Thomas R.

    IPC: G01H13/00 ,  F01D21/00 ,  G01H9/00

    CPC classification number: F01D21/003 ,  F05D2240/12 ,  F05D2240/30 ,  F05D2260/12 ,  G01H9/00 ,  G01H13/00

    Abstract: A resonant frequency testing system for airfoils 12 comprises a broach block 16, a clamp 18, an acoustic speaker 20, a laser vibrometer 22, and a control processor assembly 38. The broach block has a slot disposed to receive the airfoil in an airfoil location. The clamp 18 has a torque-actuated shutoff, and is disposed to lock the airfoil 12 in the broach block slot under a fixed clamping force. The acoustic speaker 20 is disposed adjacent the airfoil location to emit sonic pulses, and the laser vibrometer 22 is oriented towards the airfoil location to sense vibration signatures of the airfoil 12 when excited by the sonic pulses. The control processor assembly 38 is configured to control the acoustic speaker 20 and laser vibrometer 22, to decompose the sensed vibration signatures into resonant frequencies of the airfoil 12, and to store the resonant frequencies in a digital storage database, correlated with a unique ID corresponding to the airfoil.

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