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    Scalloped surface turbine stage with purge trough
    12.
    发明授权
    Scalloped surface turbine stage with purge trough 有权
    带清洗槽的扇形水轮机平台

    公开(公告)号：US09103213B2

    公开(公告)日：2015-08-11

    申请号：US13407905

    申请日：2012-02-29

    Applicant: Brian Chandler Barr ,  Brian David Keith ,  Gregory John Kajfasz ,  Prem Venugopal

    Inventor： Brian Chandler Barr ,  Brian David Keith ,  Gregory John Kajfasz ,  Prem Venugopal

    IPC: F01D5/14

    CPC classification number: F01D5/145 ,  F01D5/143 ,  F05D2240/80 ,  F05D2250/20 ,  Y02T50/673

    Abstract: A turbine stage includes a row of airfoils joined to corresponding platforms to define flow passages therebetween. Each airfoil includes opposite pressure and suction sides and extends in chord between opposite leading and trailing edges. Each platform has a scalloped flow surface including a purge trough commencing tangentially in a blend area of the platform. The purge trough extending axially toward the suction side of the airfoil, aft of the leading edge, to channel a purge flow.

    Abstract translation: 涡轮级包括连接到相应平台的一排翼型件，以限定它们之间的流动通道。 每个翼型件包括相对的压力和吸力侧面，并且在相对的前缘和后缘之间延伸成弦。 每个平台具有扇形流动表面，包括在平台的混合区域中切向开始的净化槽。 清洗槽轴向延伸到翼型的吸入侧，前缘的后部，以引导吹扫流。

    Conformal tip baffle airfoil
    14.
    发明授权
    Conformal tip baffle airfoil 有权
    保形挡板翼型

    公开(公告)号：US07686578B2

    公开(公告)日：2010-03-30

    申请号：US11507121

    申请日：2006-08-21

    Applicant: Kevin Samuel Klasing ,  Ching-Pang Lee ,  Paul Hadley Vitt ,  Brian David Keith

    Inventor： Kevin Samuel Klasing ,  Ching-Pang Lee ,  Paul Hadley Vitt ,  Brian David Keith

    IPC: F01D5/20

    CPC classification number: F01D5/20 ,  F01D5/187 ,  F05D2250/185 ,  F05D2250/70 ,  Y02T50/673 ,  Y02T50/676

    Abstract: A turbine blade includes an airfoil tip with first and second tip ribs extending from a tip floor. The ribs extend along the opposite pressure and suction sides of the blade and are joined together at opposite leading and trailing edges. A tip baffle is nested transversely between the ribs, and conforms with the second rib to bifurcate the airfoil tip into first and second tip pockets extending along the corresponding pressure and suction sides.

    Abstract translation: 涡轮机叶片包括具有从尖端底板延伸的第一和第二末端肋的翼面末端。 肋沿刀片的相对的压力和吸力侧延伸并且在相对的前缘和后缘连接在一起。 尖端挡板横向嵌套在肋之间，并且与第二肋条一致，以使翼型件尖端分叉成沿相应的压力侧和吸力侧延伸的第一和第二尖端口袋。

    Turbine blade having angled squealer tip
    17.
    发明授权
    Turbine blade having angled squealer tip 有权
    涡轮叶片具有倾斜的尖叫尖端

    公开(公告)号：US06672829B1

    公开(公告)日：2004-01-06

    申请号：US10196623

    申请日：2002-07-16

    Applicant: David Glenn Cherry ,  Ching-Pang Lee ,  Chander Prakash ,  Aspi Rustom Wadia ,  Brian David Keith ,  Steven Robert Brassfield

    Inventor： David Glenn Cherry ,  Ching-Pang Lee ,  Chander Prakash ,  Aspi Rustom Wadia ,  Brian David Keith ,  Steven Robert Brassfield

    IPC: F01D518

    CPC classification number: F01D5/141 ,  F01D5/145 ,  F01D5/20 ,  F05D2250/292

    Abstract: A turbine blade for a gas turbine engine, including an airfoil and integral dovetail for mounting the airfoil along a radial axis to a rotor disk inboard of a turbine shroud. The airfoil further includes: first and second sidewalls joined together at a leading edge and a trailing edge, where the first and second sidewalls extend from a root disposed adjacent the dovetail to a tip plate for channeling combustion gases thereover; and, at least one tip rib extending outwardly from the tip plate between the leading and trailing edges. The tip rib is oriented so that an axis extending longitudinally therethrough is at an angle with respect to the radial axis for at least a designated portion of an axial length of the turbine blade. Such angle may be substantially the same across the designated portion or may vary thereacross. Accordingly, a recirculation zone of the combustion gases is formed adjacent a distal end of the tip rib which reduces a leakage flow of the combustion gases between the airfoil and the shroud for at least the designated portion of an axial length of the turbine blade.

    Abstract translation: 一种用于燃气涡轮发动机的涡轮机叶片，包括翼型件和整体式燕尾榫，用于将翼型件沿着径向轴线安装到涡轮机外罩内侧的转子盘。 所述翼型件还包括：在前缘和后缘处连接在一起的第一和第二侧壁，其中所述第一和第二侧壁从邻近所述燕尾榫设置的根部延伸到顶板，用于在其上引导燃烧气体; 以及在前缘和后缘之间从顶板向外延伸的至少一个尖端肋。 尖端肋被定向成使得纵向延伸通过的轴线相对于径向轴线成一定角度，用于涡轮叶片的至少一个轴向长度的指定部分。 这种角度在指定部分可以是基本相同的，或者可以在其上变化。 因此，燃烧气体的再循环区域形成在尖端肋的远端附近，这减少了涡轮叶片至少轴向长度的指定部分的翼型和护罩之间的燃烧气体的泄漏流。

    Scalloped surface turbine stage
    18.
    发明授权
    Scalloped surface turbine stage 有权
    扇形水轮机平台

    公开(公告)号：US09085985B2

    公开(公告)日：2015-07-21

    申请号：US13429312

    申请日：2012-03-23

    Applicant: Brian Chandler Barr ,  Brian David Keith ,  Gregory John Kajfasz

    Inventor： Brian Chandler Barr ,  Brian David Keith ,  Gregory John Kajfasz

    IPC: F01D5/14

    CPC classification number: F01D5/143 ,  F01D5/141 ,  F01D5/145 ,  F05D2240/304 ,  F05D2250/611 ,  F05D2250/711 ,  F05D2250/712 ,  Y02T50/673

    Abstract: A turbine stage includes a row of airfoils joined to corresponding platforms to define flow passages therebetween. Each airfoil includes opposite pressure and suction sides and extends in chord between opposite leading and trailing edges. At least some of the platforms have a scalloped flow surface including a bulge adjoining the pressure side and a bowl adjoining the suction side, aft of the leading edge, of the respective airfoils. The bulge is configured having a maximum height located within its respective flow passage, and wherein the bulge decreases in height in a forward and aft direction and decreases in height laterally toward the pressure side of the airfoil and toward the bowl adjoining the suction side of a next adjacent airfoil.

    Abstract translation: 涡轮级包括连接到相应平台的一排翼型件，以限定它们之间的流动通道。 每个翼型件包括相对的压力和吸力侧面，并且在相对的前缘和后缘之间延伸成弦。 至少一些平台具有扇形流动表面，其包括邻近压力侧的凸起和邻接相应翼型件的前缘的吸力侧的碗。 凸起构造成具有位于其相应流动通道内的最大高度，并且其中凸起在前后方向上的高度减小，并且朝向翼型的压力侧横向降低，并且朝向毗邻吸入侧的碗 下一个相邻的翼型。

    SCALLOPED SURFACE TURBINE STAGE
    19.
    发明申请
    SCALLOPED SURFACE TURBINE STAGE 有权

    公开(公告)号：US20130251520A1

    公开(公告)日：2013-09-26

    申请号：US13429312

    申请日：2012-03-23

    Applicant: Brian Chandler Barr ,  Brian David Keith ,  Gregory John Kajfasz

    Inventor： Brian Chandler Barr ,  Brian David Keith ,  Gregory John Kajfasz

    IPC: F01D9/04 ,  F01D5/14

    CPC classification number: F01D5/143 ,  F01D5/141 ,  F01D5/145 ,  F05D2240/304 ,  F05D2250/611 ,  F05D2250/711 ,  F05D2250/712 ,  Y02T50/673

    Abstract: A turbine stage includes a row of airfoils joined to corresponding platforms to define flow passages therebetween. Each airfoil includes opposite pressure and suction sides and extends in chord between opposite leading and trailing edges. At least some of the platforms have a scalloped flow surface including a bulge adjoining the pressure side and a bowl adjoining the suction side, aft of the leading edge, of the respective airfoils. The bulge is configured having a maximum height located within its respective flow passage, and wherein the bulge decreases in height in a forward and aft direction and decreases in height laterally toward the pressure side of the airfoil and toward the bowl adjoining the suction side of a next adjacent airfoil.

    Abstract translation: 涡轮级包括连接到相应平台的一排翼型件，以限定它们之间的流动通道。 每个翼型件包括相对的压力和吸力侧面，并且在相对的前缘和后缘之间延伸成弦。 至少一些平台具有扇形流动表面，其包括邻近压力侧的凸起和邻接相应翼型件的前缘的吸力侧的碗。 凸起构造成具有位于其相应流动通道内的最大高度，并且其中凸起在前后方向上的高度减小，并且朝向翼型的压力侧横向降低，并且朝向毗邻吸入侧的碗 下一个相邻的翼型。

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