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公开(公告)号：US20110262695A1
公开(公告)日：2011-10-27
申请号：US12765004
申请日：2010-04-22
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）。
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公开(公告)号：US20110150653A1
公开(公告)日：2011-06-23
申请号：US12640242
申请日：2009-12-17
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）。
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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。
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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
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。
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公开(公告)号：US09810081B2
公开(公告)日：2017-11-07
申请号：US12813658
申请日：2010-06-11
CPC分类号： F01D9/023 , F02K1/822 , F05D2250/13 , F05D2250/324 , F05D2260/202 , F23M20/005 , F23R3/002 , F23R3/06 , F23R2900/00014 , F23R2900/03042 , Y02T50/675
摘要： A conduit through which hot combustion gases pass in a gas turbine engine. The conduit includes a wall structure having a central axis and defining an inner volume of the conduit for permitting hot combustion gases to pass through the conduit. The wall structure includes a forward end, an aft end axially spaced from the forward end, the aft end defining a combustion gas outlet for the hot combustion gases passing through the conduit, and a plurality of generally radially outwardly extending protuberances formed in the wall structure. The protuberances each include at least one cooling fluid passage formed therethrough for permitting cooling fluid to enter the inner volume. At least one of the protuberances is shaped so as to cause cooling fluid passing through it to diverge in a circumferential direction as it enters into the inner volume.
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公开(公告)号：US09546558B2
公开(公告)日：2017-01-17
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
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）具有与外壁的峰（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。
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公开(公告)号：US20130017095A1
公开(公告)日：2013-01-17
申请号：US13180578
申请日：2011-07-12
申请人： Ching-Pang Lee , Kok-Mun Tham , Paul H. Vitt , Stephen R. Williamson , Matthew D. Montgomery , Chander Prakash , Melissa Harris
发明人： Ching-Pang Lee , Kok-Mun Tham , Paul H. Vitt , Stephen R. Williamson , Matthew D. Montgomery , Chander Prakash , Melissa Harris
IPC分类号： F01D5/14
CPC分类号： F01D5/081 , F01D5/141 , F05D2240/81 , F05D2270/17
摘要： 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.
摘要翻译： 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 。
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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。
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公开(公告)号：US07281894B2
公开(公告)日：2007-10-16
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： F01D5/20
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。
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公开(公告)号：US06422821B1
公开(公告)日：2002-07-23
申请号：US09756902
申请日：2001-01-09
申请人： Ching-Pang Lee , Chander Prakash , Monty Lee Shelton , John Howard Starkweather , Hardev Singh , Gerard Anthony Rinck
发明人： Ching-Pang Lee , Chander Prakash , Monty Lee Shelton , John Howard Starkweather , Hardev Singh , Gerard Anthony Rinck
IPC分类号： F01D518
CPC分类号： F01D5/20 , F01D5/186 , F05D2240/121 , F05D2240/303 , F05D2250/70 , F05D2260/202
摘要： A rotor blade for a gas turbine engine including a tip region that facilitates reducing operating temperatures of the rotor blade is described. The tip region includes a first tip wall and a second tip wall extending radially outward from a tip plate of an airfoil. The tip walls extend from adjacent a leading edge of the airfoil to connect at a trailing edge of the airfoil. A notch is defined between the first and second tip walls at the airfoil leading edge. At least a portion of the second tip wall is recessed to define a tip shelf.
摘要翻译： 描述了一种用于燃气涡轮发动机的转子叶片，其包括有助于降低转子叶片的操作温度的尖端区域。 尖端区域包括从翼型件的顶板径向向外延伸的第一顶端壁和第二顶端壁。 尖端壁从翼型的前缘相邻延伸，以在翼型的后缘连接。 在翼型件前缘处的第一和第二尖端壁之间限定了切口。 第二末端壁的至少一部分被凹入以限定尖端架。
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