中科微点-全球专利检索

  1. Login
  2. Sign Up

Search Results

18 records (took 0.025 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。

    BLADE FEATURE TO SUPPORT SEGMENTED COVERPLATE
    2.
    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。

    FEATURE TO PROVIDE COOLING FLOW TO DISK
    3.
    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
    5.
    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。

    GAS TURBINE ENGINE WITH SEAL HAVING PROTRUSIONS
    6.
    发明申请
    GAS TURBINE ENGINE WITH SEAL HAVING PROTRUSIONS 审中-公开
    具有密封的气体涡轮发动机

    公开(公告)号：WO2015069362A3

    公开(公告)日：2015-07-30

    申请号：PCT/US2014052032

    申请日：2014-08-21

    Applicant: UNITED TECHNOLOGIES CORP

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

    IPC: F01D11/00 ,  F01D5/18

    CPC classification number: F01D11/006 ,  F01D5/22 ,  F05D2250/181 ,  F05D2250/182 ,  F05D2250/183 ,  F05D2250/75 ,  F05D2260/22141

    Abstract: A gas turbine engine includes a turbine section. The turbine section includes a disk that is rotatable about an axis. A plurality of turbine blades are mounted around a periphery of the disk, and a plurality of seals are arranged between the turbine blades and the periphery of the disk. Each of the seals includes, with respect to the axis, a radially outer surface and a radially inner surface. The radially inner surface includes a plurality of protrusions.

    Abstract translation: 燃气涡轮发动机包括涡轮部分。 涡轮机部分包括可围绕轴线旋转的盘。 多个涡轮机叶片围绕盘的周边安装，并且多个密封件布置在涡轮机叶片与盘周边之间。 每个密封件相对于轴线包括径向外表面和径向内表面。 径向内表面包括多个突起。

    GAS TURBINE ENGINE WITH DISK HAVING PERIPHERY WITH PROTRUSIONS
    8.
    发明申请
    GAS TURBINE ENGINE WITH DISK HAVING PERIPHERY WITH PROTRUSIONS 审中-公开
    气体涡轮发动机带有带外壳的外壳

    公开(公告)号：WO2015038305A3

    公开(公告)日：2015-05-14

    申请号：PCT/US2014051979

    申请日：2014-08-21

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： HOUGH MATTHEW ANDREW ,  BEATTIE JEFFREY S

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

    CPC classification number: F01D11/006 ,  F01D5/081 ,  F01D5/3015 ,  F01D11/003 ,  F01D11/005 ,  F01D11/008 ,  F01D11/02 ,  F01D25/12 ,  F05D2240/127 ,  F05D2240/55 ,  F05D2260/20 ,  F05D2260/2212

    Abstract: A gas turbine engine includes a turbine section that has a disk rotatable about an axis. The disk has circumferentially-spaced blade mounting features and radially outer rim surfaces extending circumferentially between the blade mounting features. Turbine blades are mounted circumferentially around the disk in the blade mounting features. Seals are arranged radially outwards of the disk adjacent the radially outer rim surfaces such that there are respective passages between the seals and the radially outer rim surfaces. The radially outer rim surfaces include radially-extending protrusions that extend into the respective passages.

    Abstract translation: 燃气涡轮发动机包括具有可绕轴线旋转的盘的涡轮部分。 盘具有周向间隔开的叶片安装特征和在叶片安装特征之间周向延伸的径向外边缘表面。 涡轮叶片在叶片安装特征中围绕圆盘周向安装。 密封件邻近径向外边缘表面布置在盘的径向外侧，使得在密封件和径向外边缘表面之间存在相应的通道。 径向外边缘表面包括延伸到相应通道中的径向延伸的突起。

    GAS TURBINE ENGINE COMPONENT WITH COMBINED MATE FACE AND PLATFORM COOLING
    9.
    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。

Patent Agency Ranking