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519 条记录 (耗时 0.027 秒)

    Conformal tip baffle airfoil
    11.
    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

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

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

    IPC分类号： F01D5/20

    CPC分类号： F01D5/20 ,  F01D5/187 ,  F05D2250/185 ,  F05D2250/70 ,  Y02T50/673 ,  Y02T50/676

    摘要： 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.

    摘要翻译： 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。

    Methods and apparatus for cooling turbine blade trailing edges
    12.
    发明授权
    Methods and apparatus for cooling turbine blade trailing edges 有权
    用于冷却涡轮叶片后缘的方法和装置

    公开(公告)号：US07387492B2

    公开(公告)日：2008-06-17

    申请号：US11312059

    申请日：2005-12-20

    申请人： Tingfan Pang ,  Ching-Pang Lee ,  Kevin Samuel Klasing ,  Steven Robert Brassfield

    发明人： Tingfan Pang ,  Ching-Pang Lee ,  Kevin Samuel Klasing ,  Steven Robert Brassfield

    IPC分类号： F01D25/12

    CPC分类号： F01D5/186 ,  F05D2240/122 ,  F05D2240/304 ,  Y02T50/676

    摘要： A method facilitates fabricating an airfoil for use with a turbine blade. The method comprises forming a substantially solid ceramic airfoil core, inserting the core into a die and casting the airfoil with a pressure side wall and a suction side wall connected together at a leading edge and a trailing edge, such that a plurality of first trailing edge slots and at least one second trailing edge slot extend from the trailing edge along the pressure side wall, wherein the second trailing edge slot has a length, measured between an inlet and an exit of the slot, that is longer than a corresponding length of each of the plurality of first trailing edge slots.

    摘要翻译： 一种方法有助于制造与涡轮叶片一起使用的翼型件。 该方法包括形成基本上固体的陶瓷翼型芯，将芯插入模具中并且在前缘和后缘连接有压力侧壁和吸力侧壁的情况下铸造翼型件，使得多个第一后缘 槽和至少一个第二后缘槽沿着所述压力侧壁从所述后缘延伸，其中所述第二后缘槽具有在所述槽的入口和出口之间测量的长度，所述长度大于每个的相应长度 的多个第一后缘槽。

    Counter tip baffle airfoil
    15.
    发明授权
    Counter tip baffle airfoil 有权
    台顶挡板翼型

    公开(公告)号：US07607893B2

    公开(公告)日：2009-10-27

    申请号：US11507132

    申请日：2006-08-21

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

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

    IPC分类号： F01D5/20

    CPC分类号： F01D5/20 ,  F01D5/145 ,  F05D2250/70 ,  Y02T50/671 ,  Y02T50/673

    摘要： A turbine blade includes an airfoil having first and second tip ribs extending along the opposite pressure and suction sides thereof. The tip ribs are spaced apart between the leading and trailing edges of the airfoil to include a tip baffle. The baffle extends chordally in counter profile with the first rib to define a first pocket, and in counter profile with the second rib to define a second pocket.

    摘要翻译： 涡轮叶片包括具有沿其相对的压力和吸力侧延伸的第一和第二末端肋的翼型件。 末端肋在翼型件的前缘和后缘之间间隔开，以包括顶端挡板。 所述挡板以第一肋条与第一肋条相反地延伸，以相反轮廓延伸，以限定第一凹槽，并且与第二肋条对置形成第二凹槽。

    Turbine airfoil with curved squealer tip
    17.
    发明授权
    Turbine airfoil with curved squealer tip 有权
    涡轮翼型具有弯曲的尖叫

    公开(公告)号：US07290986B2

    公开(公告)日：2007-11-06

    申请号：US11162433

    申请日：2005-09-09

    申请人： Mark Edward Stegemiller ,  Chander Prakash ,  Leslie Eugene Leeke ,  Kevin Samuel Klasing ,  Ching-Pang Lee

    发明人： Mark Edward Stegemiller ,  Chander Prakash ,  Leslie Eugene Leeke ,  Kevin Samuel Klasing ,  Ching-Pang Lee

    IPC分类号： F01D5/20

    CPC分类号： F01D5/20 ,  F05D2250/71 ,  F05D2250/712 ,  Y02T50/67

    摘要： 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.

    摘要翻译： 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。

    Turbine airfoil vane with an impingement insert having a plurality of impingement nozzles
    19.
    发明授权
    Turbine airfoil vane with an impingement insert having a plurality of impingement nozzles 有权
    具有冲击插入件的涡轮机翼型叶片具有多个冲击喷嘴

    公开(公告)号：US09347324B2

    公开(公告)日：2016-05-24

    申请号：US14133773

    申请日：2013-12-19

    申请人： Ching-Pang Lee

    发明人： Ching-Pang Lee

    IPC分类号： F01D5/18 ,  F01D9/04

    CPC分类号： F01D5/188 ,  F01D9/04 ,  F05D2210/33 ,  F05D2240/12 ,  F05D2240/127 ,  F05D2260/2212

    摘要： A turbine vane includes a generally elongated hollow airfoil and a cooling system. The cooling system is positioned within the airfoil and includes a cooling chamber and an impingement insert positioned in the cooling chamber. The impingement insert and an inner surface of an outer wall of the airfoil define a cooling channel therebetween. The impingement insert includes a plurality of impingement nozzles extending toward the inner surface of the outer wall and a plurality of impingement orifices. At least one of the impingement orifices is arranged in a non-aligned pattern with respect to at least one adjacent impingement orifice such that cooling fluid passing out of the at least one impingement orifice does not directly flow into a centerline of a cooling fluid flowpath of cooling fluid passing out of the at least one adjacent impingement orifice.

    摘要翻译： 涡轮叶片包括大致细长的中空翼型件和冷却系统。 冷却系统定位在翼型内，并且包括冷却室和位于冷却室中的冲击插入件。 冲击插入件和翼型件的外壁的内表面在它们之间限定冷却通道。 冲击插入件包括朝向外壁的内表面延伸的多个冲击喷嘴和多个冲击孔。 冲击孔中的至少一个相对于至少一个相邻的冲击孔布置成非对准图案，使得流出至少一个冲击孔的冷却流体不直接流入冷却流体流动路径的中心线 从至少一个相邻的冲击孔流出的冷却流体。

    Seal including flexible seal strips
    20.
    发明授权
    Seal including flexible seal strips 有权
    密封包括柔性密封条

    公开(公告)号：US09206904B2

    公开(公告)日：2015-12-08

    申请号：US12832141

    申请日：2010-07-08

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

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

    IPC分类号： F16J15/32 ,  F01D11/02

    CPC分类号： F16J15/3292 ,  F01D11/02 ,  F05D2240/57

    摘要： 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.

    摘要翻译： 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。