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    VIBRATION DAMPERS FOR TURBINE BLADES
    1.
    发明申请
    VIBRATION DAMPERS FOR TURBINE BLADES 审中-公开
    涡轮叶片振动阻尼器

    公开(公告)号：WO2015026416A3

    公开(公告)日：2015-04-16

    申请号：PCT/US2014039710

    申请日：2014-05-28

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： KNOWLTON ROBERT ,  ASTERLIN MAX ,  RAPP BRANDON M ,  JARIWALA PARTH

    IPC: F01D5/16 ,  F01D5/10

    CPC classification number: F01D5/10 ,  F01D5/081 ,  F01D5/18 ,  F01D5/26 ,  F01D11/006 ,  F05D2240/57 ,  F05D2260/96 ,  Y02T50/676

    Abstract: A turbine blade vibration damper is described. The damper has an axially-extending main body defining an inner surface and opposed damping surface. The main body also has an edge spanning from the inner surface to the damping surface and slotted apertures extending through the main body. The slotted apertures extend between the inner surface and damping surface. Adjacent pairs of slotted apertures have elongated shapes defining longitudinal axes that intersect at a point off the surface of the damper.

    Abstract translation: 描述了涡轮叶片减振器。 阻尼器具有轴向延伸的主体，其限定内表面和相对的阻尼表面。 主体还具有从内表面到阻尼表面的边缘，并且延伸穿过主体的开槽孔。 开槽孔在内表面和阻尼表面之间延伸。 相邻的开槽孔对形成了限定纵向轴线的细长形状，该轴线在阻尼器表面的一个点处相交。

    GAS TURBINE ENGINE COMPONENT WITH COMBINED MATE FACE AND PLATFORM COOLING
    2.
    发明申请
    GAS TURBINE ENGINE COMPONENT WITH COMBINED MATE FACE AND PLATFORM COOLING 审中-公开
    燃气涡轮发动机组件与组合的油面和平台冷却

    公开(公告)号：WO2014186005A3

    公开(公告)日：2015-02-26

    申请号：PCT/US2014015194

    申请日：2014-02-07

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： LEWIS SCOTT D ,  RAPP BRANDON M ,  BEATTIE JEFFREY S ,  HOUGH MATTHEW ANDREW ,  TELLER BRET M ,  JACQUES JEFFREY MICHAEL ,  ASTERLIN MAX

    IPC: F01D5/18 ,  F01D5/08 ,  F01D25/12 ,  F02C7/18 ,  F04D29/58

    CPC classification number: F01D5/186 ,  F01D9/023 ,  F05D2240/81 ,  F05D2260/202 ,  F23R3/02

    Abstract: A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a platform that axially extends between a leading edge and a trailing edge, circumferentially extends between a first mate face and a second mate face, and includes a gas path surface and a non-gas path surface. The component defines at least one cavity that extends at least partially inside of the component. A first plurality of cooling holes extends from the at least one cavity to at least one of the first mate face and the second mate face and a second plurality of cooling holes extends from either the at least one cavity or the non-gas path surface to the gas path surface.

    Abstract translation: 根据本公开的示例性方面的用于燃气涡轮发动机的部件尤其包括在前缘和后缘之间轴向延伸的平台，其周向地在第一配合面和第二配合面之间延伸，以及 包括气体通道表面和非气体通道表面。 该部件限定至少一个至少部分地在部件内部延伸的空腔。 第一多个冷却孔从所述至少一个空腔延伸到所述第一配合面和所述第二配合面中的至少一个，并且第二多个冷却孔从所述至少一个空腔或所述非气体通道表面延伸到 气路面。

    GAS TURBINE ENGINE COMPONENT WITH COMBINED MATE FACE AND PLATFORM COOLING
    4.
    发明公开
    GAS TURBINE ENGINE COMPONENT WITH COMBINED MATE FACE AND PLATFORM COOLING 有权
    GASTURBINENMOTORKOMPONENTE MIT KOMBINIERTERANPASSUNGSFLÄCHEUND PLATTFORMKHHUNG

    公开(公告)号：EP2956627A4

    公开(公告)日：2016-09-28

    申请号：EP14797049

    申请日：2014-02-07

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： LEWIS SCOTT D ,  RAPP BRANDON M ,  BEATTIE JEFFREY S ,  HOUGH MATTHEW ANDREW ,  TELLER BRET M ,  JACQUES JEFFREY MICHAEL ,  ASTERLIN MAX

    IPC: F01D5/18 ,  F01D5/08 ,  F01D11/24 ,  F01D25/12 ,  F02C7/18 ,  F04D29/58

    CPC classification number: F01D5/186 ,  F01D9/023 ,  F05D2240/81 ,  F05D2260/202 ,  F23R3/02

    Abstract: A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a platform that axially extends between a leading edge and a trailing edge, circumferentially extends between a first mate face and a second mate face, and includes a gas path surface and a non-gas path surface. The component defines at least one cavity that extends at least partially inside of the component. A first plurality of cooling holes extends from the at least one cavity to at least one of the first mate face and the second mate face and a second plurality of cooling holes extends from either the at least one cavity or the non-gas path surface to the gas path surface.

    Abstract translation: 根据本公开的示例性方面的用于燃气涡轮发动机的部件尤其包括在前缘和后缘之间轴向延伸的平台，其周向地在第一配合面和第二配合面之间延伸，以及 包括气体路径表面和非气体通道表面。 该部件限定至少一个至少部分地在部件内部延伸的空腔。 第一多个冷却孔从所述至少一个空腔延伸到所述第一配合面和所述第二配合面中的至少一个，并且第二多个冷却孔从所述至少一个空腔或非气体通道表面延伸到 气路面。

    VIBRATION DAMPERS FOR TURBINE BLADES
    5.
    发明公开
    VIBRATION DAMPERS FOR TURBINE BLADES 审中-公开
    VIBRATIONSDÄMPFERFÜRTURBINENSCHAUFELN

    公开(公告)号：EP3004557A4

    公开(公告)日：2017-02-15

    申请号：EP14837891

    申请日：2014-05-28

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： KNOWLTON ROBERT ,  ASTERLIN MAX ,  RAPP BRANDON M ,  JARIWALA PARTH

    IPC: F01D5/08 ,  F01D5/26 ,  F01D11/00

    CPC classification number: F01D5/10 ,  F01D5/081 ,  F01D5/18 ,  F01D5/26 ,  F01D11/006 ,  F05D2240/57 ,  F05D2260/96 ,  Y02T50/676

    Abstract: A turbine blade vibration damper is described. The damper has an axially-extending main body defining an inner surface and opposed damping surface. The main body also has an edge spanning from the inner surface to the damping surface and slotted apertures extending through the main body. The slotted apertures extend between the inner surface and damping surface. Adjacent pairs of slotted apertures have elongated shapes defining longitudinal axes that intersect at a point off the surface of the damper.

    Abstract translation: 描述了涡轮叶片减振器。 阻尼器具有限定内表面和相对的阻尼表面的轴向延伸主体。 主体还具有从内表面延伸到阻尼表面的边缘和延伸穿过主体的开槽孔。 开槽孔在内表面和阻尼表面之间延伸。 相邻的一对槽孔具有细长的形状，其限定纵向轴线，所述纵向轴线在阻尼器的表面处的点处相交。

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