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    Converging pin cooled airfoil
    1.
    发明申请
    Converging pin cooled airfoil 失效
    锥形冷却翼型

    公开(公告)号：US20050169752A1

    公开(公告)日：2005-08-04

    申请号：US10692700

    申请日：2003-10-24

    申请人： Ching-Pang Lee ,  Ronald Bunker ,  Chander Prakash

    发明人： Ching-Pang Lee ,  Ronald Bunker ,  Chander Prakash

    IPC分类号： F01D5/18 ,  A61B5/04

    CPC分类号： F01D5/187 ,  F05D2260/22141 ,  Y02T50/676

    摘要： A turbine airfoil includes pressure and suction sidewalls extending in chord between leading and trailing edges and in span between a root and a tip. A septum is spaced between the sidewalls to define two cooling circuits on opposite sides of the septum which converge between the leading and trailing edges. An array of pins extends inwardly from the pressure sidewall at a discharge end of the circuits, and the pins decrease in length to conform with the converging circuit.

    摘要翻译： 涡轮机翼片包括在前缘和后缘之间延伸并且在根部和尖端之间的跨度中的压力和抽吸侧壁。 隔膜间隔开在侧壁之间以在隔膜的相对侧上限定两个冷却回路，其在前缘和后缘之间会聚。 引脚阵列在电路的放电端从压力侧壁向内延伸，并且引脚的长度减小以符合会聚电路。

    Seal including flexible seal strips
    2.
    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。

    DAMPING RESONATOR WITH IMPINGEMENT COOLING
    3.
    发明申请
    DAMPING RESONATOR WITH IMPINGEMENT COOLING 有权
    阻尼谐振器与冲击冷却

    公开(公告)号：US20120006028A1

    公开(公告)日：2012-01-12

    申请号：US12832116

    申请日：2010-07-08

    申请人： Ching-Pang Lee ,  Danning You ,  Reinhard Schilp ,  Chander Prakash

    发明人： Ching-Pang Lee ,  Danning You ,  Reinhard Schilp ,  Chander Prakash

    IPC分类号： F02C7/24 ,  F02C7/12

    CPC分类号： F01D9/023 ,  F02C7/12 ,  F05D2260/96 ,  F23R3/06 ,  F23R2900/00014

    摘要： A resonance chamber (42) has an outer wall (32) with coolant inlet holes (34A-C), an inner wall (36) with acoustic holes (38), and side walls (40A-C) between the inner and outer walls. A depression (33A-C) in the outer wall has a bottom portion (50) that is close to the inner wall compared to peaks (37A-C) of the outer wall. The coolant inlet holes may be positioned along the bottom portion of the depression and along a bottom portion of the side walls to direct coolant flows (44, 51) toward impingement locations (43) on the inner wall that are out of alignment with the acoustic holes. This improves impingement cooling efficiency. The peaks (37A-C) of the outer wall provide volume in the resonance chamber for a target resonance.

    摘要翻译： 共振室（42）具有外壁（32），其具有冷却剂入口孔（34A-C），具有声孔（38）的内壁（36）和内壁和外壁之间的侧壁（40A-C） 。 外壁上的凹部（33A-C）具有与外壁的顶部（37A-C）相比靠近内壁的底部部分（50）。 冷却剂入口孔可以沿着凹陷的底部部分并且沿着侧壁的底部部分定位，以将冷却剂流（44,41）引向内壁上与声学不对准的冲击位置（43） 孔。 这提高了冲击冷却效率。 外壁的峰（37A-C）在共振室中提供用于目标共振的体积。

    Discreetly Defined Porous Wall Structure for Transpirational Cooling
    4.
    发明申请
    Discreetly Defined Porous Wall Structure for Transpirational Cooling 有权
    用于旋转冷却的谨慎定义的多孔壁结构

    公开(公告)号：US20110262695A1

    公开(公告)日：2011-10-27

    申请号：US12765004

    申请日：2010-04-22

    申请人： Ching-Pang Lee ,  Chander Prakash ,  Gary B. Merrill ,  Andreas Heselhaus ,  Andrew J. Burns

    发明人： Ching-Pang Lee ,  Chander Prakash ,  Gary B. Merrill ,  Andreas Heselhaus ,  Andrew J. Burns

    IPC分类号： B32B3/10

    CPC分类号： F01D5/182 ,  B33Y80/00 ,  F01D5/183 ,  F01D5/184 ,  F05D2230/22 ,  F05D2230/90 ,  F05D2250/18 ,  F05D2250/185 ,  F05D2250/28 ,  F05D2250/30 ,  F05D2260/203 ,  F05D2260/221 ,  Y10T428/24273

    摘要： A wall structure (32, 42, 68, 70, 80) with layers (A, B, C, D, E) of non-random voids (26A, 26B, 28B, 30B) that interconnect to form discretely defined tortuous passages between an interior (21) and an exterior surface (23) of the wall for transpiration cooling of the wall. A coolant flow (38) through the wall may be metered by restrictions in coolant outlets (31) and/or within the passages to minimize the coolant requirement. Pockets (44) may be formed on the exterior surface of the wall for thermal Insulation (46). The layers may be formed by lamination, additive manufacturing, or casting. Layer geometries include alternating layers (A, B, C) with different overlapping void patterns (42), 3-D lattice structures (70), and offset waffle structures (80).

    摘要翻译： 具有非随机空隙（26A，26B，28B，30B）的层（A，B，C，D，E）的壁结构（32,42,68,70,80），其互连以在 所述壁的内部（21）和外表面（23）用于所述壁的蒸发冷却。 通过壁的冷却剂流（38）可以通过冷却剂出口（31）和/或通道内的限制来计量，以使冷却剂需求最小化。 口袋（44）可以形成在隔热壁的外表面上（46）。 层可以通过层压，添加剂制造或铸造形成。 层几何形状包括具有不同重叠空白图案（42），3-D网格结构（70）和偏置华夫饼结构（80）的交替层（A，B，C）。

    Plasma Induced Flow Control of Boundary Layer at Airfoil Endwall
    5.
    发明申请
    Plasma Induced Flow Control of Boundary Layer at Airfoil Endwall 失效
    翼型端壁边界层等离子体诱导流量控制

    公开(公告)号：US20110150653A1

    公开(公告)日：2011-06-23

    申请号：US12640242

    申请日：2009-12-17

    申请人： Matthew D. Montgomery ,  Ching-Pang Lee ,  Chander Prakash

    发明人： Matthew D. Montgomery ,  Ching-Pang Lee ,  Chander Prakash

    IPC分类号： F01D5/14 ,  F01D9/02

    CPC分类号： F01D5/145 ,  F05D2270/172 ,  Y02T50/67 ,  Y02T50/673

    摘要： Plasma generators (48, 49, 70, 71) in an endwall (25) of an airfoil (22) induce aerodynamic flows in directions (50) that modify streamlines (47) of the endwall boundary layer toward a streamline geometry (46) of a midspan region of the airfoil. This reduces vortices (42) generated by the momentum deficit of the boundary layer, increasing aerodynamic efficiency. The plasma generators may be arrayed around the leading edge as well as between two airfoils (22) in a gas turbine nozzle structure, and may be positioned at correction points (68) in streamlines caused by surface contouring (66) of the endwall. The plasma generators may be oriented to generate flow vectors (74) that combine with boundary layer flow vectors (72) to produce resultant flow vectors (76) in directions that reduce turbulence.

    摘要翻译： 翼型件（22）的端壁（25）中的等离子体发生器（48,49,70,71）在方向（50）上引起空气动力学流动，所述方向（50）将端壁边界层的流线（47）改变为流线几何形状（46） 翼型的跨跨区域。 这减少了由边界层的动量缺失产生的旋涡（42），从而提高了空气动力学效率。 等离子体发生器可以围绕前缘以及在燃气涡轮喷嘴结构中的两个翼型件（22）之间排列，并且可以位于由端壁的表面轮廓（66）引起的流线中的校正点（68）处。 等离子体发生器可以被定向以产生与边界层流向量（72）组合的流向量（74），以在减少湍流的方向上产生合成流向量（76）。

    Turbine assembly for a gas turbine engine and method of manufacturing the same
    6.
    发明授权
    Turbine assembly for a gas turbine engine and method of manufacturing the same 有权
    用于燃气涡轮发动机的涡轮组件及其制造方法

    公开(公告)号：US07758306B2

    公开(公告)日：2010-07-20

    申请号：US11615514

    申请日：2006-12-22

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

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

    IPC分类号： F01D1/02

    CPC分类号： F01D9/041 ,  F01D5/141 ,  F01D5/145 ,  Y02T50/673 ,  Y10T29/49236

    摘要： 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.

    摘要翻译： 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 AIRFOIL CURVED SQUEALER TIP WITH TIP SHELF
    8.
    发明申请
    TURBINE AIRFOIL CURVED SQUEALER TIP WITH TIP SHELF 有权
    涡轮机空气IL ED SQ SQ SQ。。。。。。。

    公开(公告)号：US20070059173A1

    公开(公告)日：2007-03-15

    申请号：US11162434

    申请日：2005-09-09

    申请人： Ching-Pang Lee ,  Chander Prakash

    发明人： Ching-Pang Lee ,  Chander Prakash

    IPC分类号： F01D5/18

    CPC分类号： F01D5/20 ,  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. At least a portion of the pressure-side tip wall is recessed from the pressure sidewall to define an outwardly facing tip shelf, such that the pressure-side tip wall and the tip shelf define a trough therebetween.

    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。 压力侧顶端壁的至少一部分从压力侧壁凹入以限定向外的顶端架，使得压力侧顶端壁和尖端架在其间限定槽。

    SEAL INCLUDING FLEXIBLE SEAL STRIPS
    10.
    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

    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： F02F11/00 ,  F16J15/44

    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。