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    SEAL INCLUDING FLEXIBLE SEAL STRIPS
    2.
    发明申请
    SEAL INCLUDING FLEXIBLE SEAL STRIPS 有权
    密封包括柔性密封条

    公开(公告)号：US20120007318A1

    公开(公告)日：2012-01-12

    申请号：US12832141

    申请日：2010-07-08

    Applicant: Ching-Pang Lee ,  Vincent P. Laurello ,  Chander Prakash ,  Kok-Mun Tham

    Inventor： Ching-Pang Lee ,  Vincent P. Laurello ,  Chander Prakash ,  Kok-Mun Tham

    IPC: F02F11/00 ,  F16J15/44

    CPC classification number: F16J15/3292 ,  F01D11/02 ,  F05D2240/57

    Abstract: A seal member for effecting a seal preventing fluid flow in an axial direction through an annular space formed between two relatively moving components including a rotatable shaft and a stator structure. The seal member includes a plurality of flexible seal strips. Each seal strip includes a planar plate extending radially through the annular space and having a radially outer end supported to the stator structure and a radially inner end defining a tip portion extending widthwise in the axial direction engaged in sliding contact with a peripheral surface of the rotatable shaft. At least one of the seal strips includes a plurality of perforations extending through the seal strip and located between a leading edge and a trailing edge of the seal strip for effecting an increased flexibility of the seal strip adjacent to the tip portion.

    Abstract translation: 一种用于实现密封的密封件，其防止流体沿轴向流动通过形成在包括可旋转轴和定子结构的两个相对移动部件之间的环形空间。 密封构件包括多个柔性密封条。 每个密封条包括平面板，该平面板径向地延伸穿过环形空间并且具有支撑到定子结构的径向外端，以及限定沿轴向方向沿宽度方向延伸的尖端部分的径向内端，该尖端部分与可旋转的 轴。 密封条中的至少一个包括延伸穿过密封条并且位于密封条的前缘和后缘之间的多个穿孔，用于实现与尖端部分相邻的密封条的增加的柔性。

    TURBINE AIRFOIL WITH CURVED SQUEALER TIP
    5.
    发明申请
    TURBINE AIRFOIL WITH CURVED SQUEALER TIP 有权
    涡轮发动机带有弯曲的螺母提示

    公开(公告)号：US20070059182A1

    公开(公告)日：2007-03-15

    申请号：US11162433

    申请日：2005-09-09

    Applicant: Mark Stegemiller ,  Chander Prakash ,  Leslie Leeke ,  Kevin Klasing ,  Ching-Pang Lee

    Inventor： Mark Stegemiller ,  Chander Prakash ,  Leslie Leeke ,  Kevin Klasing ,  Ching-Pang Lee

    IPC: B64C27/46

    CPC classification number: F01D5/20 ,  F05D2250/71 ,  F05D2250/712 ,  Y02T50/67

    Abstract: An airfoil for a gas turbine engine includes a root, a tip, a leading edge, a trailing edge, and opposed pressure and suction sidewalls extending generally along a radial axis. The airfoil includes a tip cap extending between the pressure and suction sidewalls; and spaced-apart suction-side and pressure-side tip walls extending radially outward from the tip cap to define a tip cavity therebetween. The pressure-side tip wall includes a continuously concave curved arcuate portion, at least a section of which extends circumferentially outward from a radial axis of the airfoil.

    Abstract translation: 用于燃气涡轮发动机的翼型件包括根部，尖端，前缘，后缘以及大致沿径向轴线延伸的相对的压力和吸力侧壁。 翼型件包括在压力侧和吸力侧壁之间延伸的顶盖; 并且间隔开的吸入侧和压力侧尖端壁从尖端帽径向向外延伸以在它们之间限定尖端腔。 压力侧末端壁包括连续凹入的弯曲弧形部分，其至少一部分从翼型件的径向轴向向外延伸。

    Triple circuit turbine blade
    6.
    发明授权
    Triple circuit turbine blade 失效
    三回路涡轮叶片

    公开(公告)号：US06984103B2

    公开(公告)日：2006-01-10

    申请号：US10718465

    申请日：2003-11-20

    Applicant: Ching-Pang Lee ,  Steven Robert Brassfield ,  Chander Prakash

    Inventor： Ching-Pang Lee ,  Steven Robert Brassfield ,  Chander Prakash

    IPC: F03D11/00

    CPC classification number: F01D5/187 ,  Y02T50/673 ,  Y02T50/676

    Abstract: A turbine blade includes an airfoil having pressure and suction sidewalls extending between leading and trailing edges, and from root to tip. A dovetail is joined to the airfoil root at a platform. Three internal cooling circuits extend in span inside the airfoil, and each circuit includes a respective inlet channel commencing in axially adjacent alignment in the dovetail. The inlet channels twist together from the dovetail, through the platform, and into the airfoil behind the leading edge in transverse adjacent alignment across the sidewalls.

    Abstract translation: 涡轮叶片包括具有在前缘和后缘之间延伸的压力和吸力侧壁以及从根部到尖端的翼型件。 燕尾榫在平台上连接到翼型根部。 三个内部冷却回路在翼型内部的跨度上延伸，并且每个回路包括相应的入口通道，其从燕尾榫开始轴向相邻对准。 入口通道从燕尾榫通过平台扭转在一起，并且横跨相邻的侧壁横向相邻对齐，并进入前缘的后翼。

    Flow directing member for gas turbine engine
    7.
    发明授权
    Flow directing member for gas turbine engine 有权
    燃气轮机发动机导流构件

    公开(公告)号：US08721291B2

    公开(公告)日：2014-05-13

    申请号：US13180578

    申请日：2011-07-12

    Applicant: Ching-Pang Lee ,  Kok-Mun Tham ,  Paul H. Vitt ,  Stephen R. Williamson ,  Matthew D. Montgomery ,  Chander Prakash ,  Melissa Harris

    Inventor： Ching-Pang Lee ,  Kok-Mun Tham ,  Paul H. Vitt ,  Stephen R. Williamson ,  Matthew D. Montgomery ,  Chander Prakash ,  Melissa Harris

    IPC: F01D5/14

    CPC classification number: F01D5/081 ,  F01D5/141 ,  F05D2240/81 ,  F05D2270/17

    Abstract: In a gas turbine engine, a flow directing member includes a platform supported on a rotor and includes a radially facing endwall and at least one axially facing axial surface extending radially inwardly from a junction with the endwall. The flow directing member further includes an airfoil extending radially outwardly from the endwall and a fluid flow directing feature. The fluid flow directing feature includes a groove extending axially into the axial surface. The groove has a radially inner groove end and a radially outer groove end, wherein the outer groove end defines an axially extending notch in the junction between the axial surface and the endwall and forms an opening in the endwall for directing a cooling fluid to the endwall.

    Abstract translation: 在燃气涡轮发动机中，流动引导构件包括支撑在转子上的平台，并且包括径向面向的端壁和至少一个轴向面向轴向表面，该轴向表面从与所述端壁的连接处径向向内延伸。 导流构件还包括从端壁径向向外延伸的翼型件和流体流动引导构件。 流体流动导向特征包括轴向延伸到轴向表面的凹槽。 凹槽具有径向内槽端部和径向外槽端部，其中外槽端部在轴向表面和端壁之间的连接处限定轴向延伸的凹口，并在端壁中形成开口，用于将冷却流体引导到端壁 。

    TURBINE ASSEMBLY FOR A GAS TURBINE ENGINE AND METHOD OF MANUFACTURING THE SAME
    9.
    发明申请
    TURBINE ASSEMBLY FOR A GAS TURBINE ENGINE AND METHOD OF MANUFACTURING THE SAME 有权
    用于气体涡轮发动机的涡轮组件及其制造方法

    公开(公告)号：US20080148564A1

    公开(公告)日：2008-06-26

    申请号：US11615514

    申请日：2006-12-22

    Applicant: Scott Andrew Burton ,  Chander Prakash ,  Joseph Machnaim ,  David Glenn Cherry ,  Robert John Beacock ,  Ching-Pang Lee ,  Scott Michael Carson

    Inventor： Scott Andrew Burton ,  Chander Prakash ,  Joseph Machnaim ,  David Glenn Cherry ,  Robert John Beacock ,  Ching-Pang Lee ,  Scott Michael Carson

    IPC: F01D5/02

    CPC classification number: F01D9/041 ,  F01D5/141 ,  F01D5/145 ,  Y02T50/673 ,  Y10T29/49236

    Abstract: A turbine assembly for a gas turbine engine. The turbine assembly includes at least one stator assembly including a radially inner band and at least one stator vane that extends radially outward from the inner band. The stator vane includes an airfoil having a root portion adjacent to the inner band and a tip portion. The airfoil also includes at least one lean directional change that is defined between the root portion and the tip portion. The turbine assembly also includes at least one turbine blade assembly that includes at least one rotor blade. The blade assembly is coupled in flow communication with the stator assembly such that an axial spacing is defined therebetween. The axial spacing defined adjacent to the at least one lean directional change is wider than the axial spacing defined adjacent to the root portion.

    Abstract translation: 一种用于燃气涡轮发动机的涡轮组件。 涡轮机组件包括至少一个定子组件，其包括径向内部带和至少一个定子叶片，其从内部带径向向外延伸。 定子叶片包括具有与内带相邻的根部部分和尖端部分的翼型件。 翼型件还包括限定在根部部分和尖端部分之间的至少一个精简方向变化。 涡轮组件还包括至少一个包括至少一个转子叶片的涡轮叶片组件。 叶片组件与定子组件流体连通地联接，使得在它们之间限定轴向间隔。 与所述至少一个瘦方向变化相邻限定的轴向间隔比邻近根部限定的轴向间隔宽。

    Turbine blade having angled squealer tip
    10.
    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。

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