中科微点-全球专利检索

  1. Login
  2. Sign Up

Search Results

30 records (took 0.024 seconds)

    GAS TURBINE ENGINE COMPONENT WITH COMBINED MATE FACE AND PLATFORM COOLING
    1.
    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。

    FEATURE TO PROVIDE COOLING FLOW TO DISK
    2.
    发明申请
    FEATURE TO PROVIDE COOLING FLOW TO DISK 审中-公开
    提供冷却流的特点

    公开(公告)号：WO2015073112A3

    公开(公告)日：2015-08-20

    申请号：PCT/US2014056023

    申请日：2014-09-17

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： BEATTIE JEFFREY S ,  HIMES JASON D ,  HOUGH MATTHEW ANDREW ,  CORCORAN CHRISTOPHER

    IPC: F01D5/08 ,  F01D5/18

    CPC classification number: F01D5/081 ,  F01D5/082 ,  F01D5/085 ,  F01D5/12 ,  F01D5/187 ,  F01D5/3007 ,  F01D5/3015 ,  F05D2220/32 ,  F05D2240/81 ,  F05D2260/20

    Abstract: An assembly according to an exemplary aspect of the present disclosure includes, among other things, a disk, a cover plate providing a cavity at a first axial side of the disk, a passageway including an inlet provided by a notch in at least one of the disk and the cover plate in fluid communication with the cavity, and the passageway extending from the inlet to an exit provided at a second axial side of the disk opposite the first axial side, the exit in fluid communication with the inlet, and the passageway configured to provide fluid flow from the cavity to the exit.

    Abstract translation: 根据本公开的示例性方面的组件包括盘，在盘的第一轴向侧提供空腔的盖板，包括由至少一个中的至少一个中的凹口提供的入口的通道 盘和盖板与空腔流体连通，并且从入口延伸到设置在与第一轴向侧相对的盘的第二轴向侧处的出口的通道，与入口流体连通的出口和配置的通道 以提供从空腔到出口的流体流动。

    PLATFORM COOLING CORE FOR A GAS TURBINE ENGINE ROTOR BLADE
    3.
    发明申请
    PLATFORM COOLING CORE FOR A GAS TURBINE ENGINE ROTOR BLADE 审中-公开
    用于燃气轮机发动机转子叶片的平台冷却芯

    公开(公告)号：WO2015057310A3

    公开(公告)日：2015-07-30

    申请号：PCT/US2014053042

    申请日：2014-08-28

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： HOUGH MATTHEW ANDREW ,  BEATTIE JEFFREY S

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

    CPC classification number: F01D5/187 ,  F05D2240/81 ,  F05D2260/201 ,  F05D2260/2212

    Abstract: A rotor blade according to an exemplary aspect of the present disclosure includes, among other things, a platform, an airfoil that extends from the platform, a first cooling core that extends at least partially inside the airfoil, a second cooling core inside of the platform and a first cooling hole that extends between a mate face of the platform and the second cooling core.

    Abstract translation: 除了别的之外，根据本公开的示例性方面的转子叶片包括平台，从平台延伸的翼型件，至少部分地在翼型件内部延伸的第一冷却芯件，平台内的第二冷却芯件 以及在平台的配合面和第二冷却芯之间延伸的第一冷却孔。

    BLADE FEATURE TO SUPPORT SEGMENTED COVERPLATE
    5.
    发明申请
    BLADE FEATURE TO SUPPORT SEGMENTED COVERPLATE 审中-公开
    刀片功能支持分段的封面

    公开(公告)号：WO2015112226A3

    公开(公告)日：2015-10-08

    申请号：PCT/US2014064041

    申请日：2014-11-05

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： HOUGH MATTHEW ANDREW ,  CORCORAN CHRISTOPHER ,  BEATTIE JEFFREY S

    IPC: F01D5/14 ,  F01D5/30

    CPC classification number: F01D5/3015 ,  F01D25/005 ,  F05D2220/32 ,  Y02T50/671

    Abstract: A gas turbine engine component comprises a blade having a leading edge and a trailing edge. The blade is mounted to a disc and configured for rotation about an axis. A platform supports the blade, and has a fore edge portion at the leading edge and an aft edge portion at the trailing edge. At least one of the fore edge portion and aft edge portion includes a mouth portion defined by an inner wing and an outer wing spaced radially outward of the inner wing. At least one coverplate is retained against the disc by the inner wing. A gas turbine engine is also disclosed.

    Abstract translation: 燃气涡轮发动机部件包括具有前缘和后缘的叶片。 刀片安装在光盘上并配置为绕轴旋转。 平台支撑叶片，并具有在前缘处的前缘部分和在后缘处的后缘部分。 前缘部分和后缘部分中的至少一个包括由内翼和与内翼径向向外间隔开的外翼限定的口部。 至少一个盖板通过内翼被保持在盘上。 燃气涡轮发动机也被公开。

    TURBINE BLADE ROOT PROFILE
    6.
    发明申请
    TURBINE BLADE ROOT PROFILE 审中-公开
    涡轮叶片根部轮廓

    公开(公告)号：WO2014099082A3

    公开(公告)日：2014-08-28

    申请号：PCT/US2013061920

    申请日：2013-09-26

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： BEATTIE JEFFREY S ,  JACQUES JEFFREY MICHAEL

    IPC: F01D5/14 ,  F01D5/20 ,  F02C3/14 ,  F02C7/20

    CPC classification number: F01D5/30 ,  F01D5/18 ,  F01D5/3007

    Abstract: A turbine blade for a gas turbine engine includes an airfoil that extends in a first radial direction from a platform. A root extends from the platform in a second radial direction and has opposing lateral sides that provide a firtree-shaped contour. The contour includes first, second and third lobes on each of the lateral sides and that tapers relative to the radial direction away from the platform. The first, second and third lobes each provide contact surfaces arranged at about 45° relative to the radial direction. A contact plane on each lateral side at an angle of about 11° relative to the radial direction defining a contact point on each of the contact surfaces. The first, second and third lobes each include first, second and third grooves that are substantially aligned with one another along an offset plane spaced a uniform offset distance from the contact plane.

    Abstract translation: 用于燃气涡轮发动机的涡轮机叶片包括从平台沿第一径向方向延伸的翼型件。 根部沿第二径向方向从平台延伸，并具有提供冷杉状轮廓的相对侧面。 轮廓包括在每个横向侧上的第一，第二和第三凸角，并且所述轮廓相对于远离平台的径向方向逐渐变细。 第一，第二和第三凸角各自提供相对于径向方向布置成约45°的接触表面。 在每个侧面上相对于径向方向成约11°角的接触面​​限定了每个接触面上的接触点。 第一，第二和第三瓣各自包括第一，第二和第三槽，所述第一，第二和第三槽沿着与接触平面间隔均匀偏移距离的偏移平面彼此基本对齐。

    TURBINE BLADE ROOT WITH MICROCIRCUIT COOLING PASSAGES
    8.
    发明专利
    TURBINE BLADE ROOT WITH MICROCIRCUIT COOLING PASSAGES 未知

    公开(公告)号：SG11201407921VA

    公开(公告)日：2015-01-29

    申请号：SG11201407921V

    申请日：2013-05-20

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： BEATTIE JEFFREY S ,  JACQUES JEFFREY MICHAEL ,  PIGGUSH JUSTIN D

    IPC: F01D5/18

    Abstract: A method of fabricating an airfoil includes the steps of fabricating a first core including a first plurality of ribs defining a first plurality of passages of a completed airfoil, and fabricating as second core including a second plurality of ribs defining a second plurality of passages of the completed airfoil. The second plurality of ribs includes a plurality of standoffs. The plurality of standoffs set a spacing between the first plurality of ribs and the second plurality of ribs to define a spacing between the first plurality of channels and the second plurality of channels of the completed airfoil. The airfoil is then molded about the core assembly. Once completed, the core assembly is removed to provide a completed airfoil incorporating multiple microcircuits with a desired stability and structural integrity.

    ROTOR BLADE PLATFORM COOLING PASSAGE
    10.
    发明申请
    ROTOR BLADE PLATFORM COOLING PASSAGE 审中-公开
    转子叶片平台冷却通道

    公开(公告)号：WO2015112240A3

    公开(公告)日：2015-10-29

    申请号：PCT/US2014065857

    申请日：2014-11-17

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： SNYDER DANIEL A ,  BEATTIE JEFFREY S

    IPC: F01D5/18 ,  F02C7/18

    CPC classification number: F01D5/187 ,  F01D5/186 ,  F01D11/006 ,  F04D29/324 ,  F04D29/582 ,  F05D2240/81 ,  F05D2260/201 ,  F05D2260/202 ,  Y02T50/676

    Abstract: A rotor blade according to an exemplary aspect of the present disclosure includes, among other things, a platform, an airfoil that extends from the platform and a platform cooling passage extending inside of the platform. The platform cooling passage includes an inlet disposed through a non-gas path surface of the platform and an outlet disposed through a mate face of the platform.

    Abstract translation: 根据本公开的示例性方面的转子叶片包括平台，从平台延伸的翼型件和在平台内延伸的平台冷却通道。 平台冷却通道包括通过平台的非气体通道表面设置的入口和通过平台的配合面设置的出口。

Patent Agency Ranking