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91. 发明授权

US07901182B2 Near wall cooling for a highly tapered turbine blade 有权
标题翻译：用于高锥度涡轮叶片的近壁冷却
公开(公告)号：US07901182B2
公开(公告)日：2011-03-08
申请号：US11804434
申请日：2007-05-18
申请人： George Liang
发明人： George Liang
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F05D2260/22141
摘要： A turbine blade having a pressure sidewall and a suction sidewall connected at chordally spaced leading and trailing edges to define a cooling cavity. Pressure and suction side inner walls extend radially within the cooling cavity and define pressure and suction side near wall chambers. A plurality of mid-chord channels extend radially from a radially intermediate location on the blade to a tip passage at the blade tip for connecting the pressure side and suction side near wall chambers in fluid communication with the tip passage. In addition, radially extending leading edge and trailing edge flow channels are located adjacent to the leading and trailing edges, respectively, and cooling fluid flows in a triple-pass serpentine path as it flows through the leading edge flow channel, the near wall chambers and the trailing edge flow channel.
摘要翻译：涡轮叶片具有压力侧壁和抽吸侧壁，连接在弦向间隔的前缘和后缘以限定冷却腔。压力和吸力侧内壁在冷却腔内径向延伸，并在壁室附近限定压力和吸力侧。多个中和弦通道从叶片上的径向中间位置径向延伸到叶片尖端处的尖端通道，用于连接与顶端通道流体连通的靠近壁室的压力侧和吸力侧。此外，径向延伸的前缘和后缘流动通道分别位于前缘和后缘附近，并且冷却流体在流过前缘流动通道，近壁室和后缘流动通道。

92. 发明申请

US20110033312A1 COMPOUND COOLING FLOW TURBULATOR FOR TURBINE COMPONENT 有权
标题翻译：涡轮组件的复合冷却流量涡轮机
公开(公告)号：US20110033312A1
公开(公告)日：2011-02-10
申请号：US12884464
申请日：2010-09-17
申请人： Ching-Pang Lee , Nan Jiang , John J. Marra , Ronald J. Rudolph
发明人： Ching-Pang Lee , Nan Jiang , John J. Marra , Ronald J. Rudolph
IPC分类号： F01D5/18
CPC分类号： F01D5/18 , F01D5/187 , F05D2250/181 , F05D2250/60 , F05D2250/611 , F05D2250/70 , F05D2250/711 , F05D2250/712 , F05D2260/2212 , F05D2260/22141
摘要： Multi-scale turbulation features, including first turbulators (46, 48) on a cooling surface (44), and smaller turbulators (52, 54, 58, 62) on the first turbulators. The first turbulators may be formed between larger turbulators (50). The first turbulators may be alternating ridges (46) and valleys (48). The smaller turbulators may be concave surface features such as dimples (62) and grooves (54), and/or convex surface features such as bumps (58) and smaller ridges (52). An embodiment with convex turbulators (52, 58) in the valleys (48) and concave turbulators (54, 62) on the ridges (46) increases the cooling surface area, reduces boundary layer separation, avoids coolant shadowing and stagnation, and reduces component mass.
摘要翻译：多尺度紊流特征，包括在冷却表面（44）上的第一湍流器（46,48）和在第一湍流器上的较小湍流器（52,54,58,62）。可以在较大的湍流器（50）之间形成第一湍流器。第一个紊流器可以是交替的脊（46）和谷（48）。较小的湍流器可以是诸如凹坑（62）和凹槽（54）的凹表面特征，和/或诸如凸块（58）和较小脊（52）的凸表面特征。在脊（46）上的谷（48）和凹形湍流器（54,62）中具有凸起的湍流器（52,58）的实施例增加了冷却表面面积，减少了边界层分离，避免了冷却剂遮蔽和停滞，并且减少了部件质量

93. 发明申请

US20110033311A1 Turbine Airfoil Cooling System with Pin Fin Cooling Chambers 审中-公开
标题翻译：涡轮机翼型冷却系统，带散热片冷却室
公开(公告)号：US20110033311A1
公开(公告)日：2011-02-10
申请号：US12536869
申请日：2009-08-06
申请人： Nicholas F. Martin , John J. Marra , Melissa Seco-Soley
发明人： Nicholas F. Martin , John J. Marra , Melissa Seco-Soley
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F05D2240/122 , F05D2240/304 , F05D2250/60 , F05D2260/2212 , F05D2260/22141
摘要： A cooling system for a turbine airfoil having at least one pin fin with a dimpled outer surface is disclosed. The dimpled outer surface increases the cooling efficiency of the pin fin, which creates numerous efficiencies, including thermal efficiencies, manufacturing efficiencies and the like. The dimples may be formed from shapes including, but not limited to, circular, oval, racetrack, and hemispherical. The dimples may be aligned in a variety of configurations.
摘要翻译：公开了一种具有至少一个具有凹陷的外表面的销翅片的用于涡轮机翼型的冷却系统。凹凸的外表面增加了销翅片的冷却效率，这产生了许多效率，包括热效率，制造效率等。凹坑可以由包括但不限于圆形，椭圆形，跑道和半球形的形状形成。凹坑可以以各种配置对准。

94. 发明授权

US07866947B2 Turbine blade trip strip orientation 有权
标题翻译：涡轮叶片脱扣条取向
公开(公告)号：US07866947B2
公开(公告)日：2011-01-11
申请号：US11648929
申请日：2007-01-03
申请人： Edward F. Pietraszkiewicz , James P. Downs
发明人： Edward F. Pietraszkiewicz , James P. Downs
IPC分类号： F01D5/18 , F01D25/12
CPC分类号： F01D5/186 , F01D5/188 , F05D2240/126 , F05D2240/127 , F05D2250/183 , F05D2250/314 , F05D2260/2212 , F05D2260/2214 , F05D2260/22141 , Y02T50/676
摘要： A turbine component includes a coolant passage and a plurality of trip members that extend within the coolant passage. Each of the plurality of trip members includes an orientation relative to an expected flow direction through the coolant passage. At least three of the trip members have orientations that are different from each other. For example, the orientations of the trip members progressively transition along the length of the coolant passage.
摘要翻译：涡轮机部件包括在冷却剂通道内延伸的冷却剂通道和多个跳闸部件。多个跳闸构件中的每一个包括相对于穿过冷却剂通道的预期流动方向的取向。至少三个跳闸构件具有彼此不同的取向。例如，跳闸构件的取向沿着冷却剂通道的长度逐渐过渡。

95. 发明申请

US20100303635A1 COOLING ARRANGEMENTS 有权
标题翻译：冷却安排
公开(公告)号：US20100303635A1
公开(公告)日：2010-12-02
申请号：US12787758
申请日：2010-05-26
申请人： Roderick M. TOWNES , Ian Tibbott , Edwin Dane , Caner H. Helvaci
发明人： Roderick M. TOWNES , Ian Tibbott , Edwin Dane , Caner H. Helvaci
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F05D2250/11 , F05D2250/70 , F05D2260/2212 , F05D2260/22141
摘要： Providing cooling within hollow blades such as high pressure turbine blades in a gas turbine engine is important to maintain these components within operational margins for the materials from which they are formed. Traditionally, coolant flows in hollow passages have been used along with impingement apertures towards a leading passage for cooling effectiveness. It is known that opposed undulations or ribs can create rotational vortices within the passage. By shaping shaped portions between the opposed undulations and possibly providing undulations upon these shaped portions themselves it is possible to generate stronger more powerful vortices within the passage. These vortices are coupled with the impingement orifices to create proportionally greater impingement jet flow and pressure and therefore cooling effectiveness within the leading passage.
摘要翻译：在诸如燃气轮机发动机中的高压涡轮机叶片的中空叶片内提供冷却对于将这些部件保持在其形成的材料的操作边缘内是重要的。传统上，在中空通道中的冷却剂流已经与冲击孔一起使用，朝向前导通道以降低冷却效果。已知相对的起伏或肋可以在通道内产生旋转涡流。通过在相对的波纹之间成形成形部分并且可能在这些成形部分本身上提供起伏，可以在通道内产生更强大的更强大的涡流。这些涡流与冲击孔结合，以产生比例地更大的冲击射流和压力，从而在前导通道内产生冷却效果。

96. 发明授权

US07819629B2 Blade for a gas turbine 有权
标题翻译：燃气轮机叶片
公开(公告)号：US07819629B2
公开(公告)日：2010-10-26
申请号：US11707227
申请日：2007-02-15
申请人： George Liang
发明人： George Liang
IPC分类号： F01D5/08
CPC分类号： F01D5/187 , F05D2240/81 , F05D2260/2212 , F05D2260/22141
摘要： A blade is provided for a gas turbine. The blade comprises a main body comprising a cooling fluid entrance channel; a cooling fluid collector in communication with the cooling fluid entrance channel; a plurality of side channels extending through an outer wall of the main body and communicating with the cooling fluid collector and a cooling fluid cavity; a cooling fluid exit channel communicating with the cooling fluid cavity; and a plurality of exit bores extending from the cooling fluid exit channel through the main body outer wall.
摘要翻译：为燃气轮机提供叶片。叶片包括主体，其包括冷却流体入口通道; 与冷却流体入口通道连通的冷却流体收集器; 多个侧通道，其延伸穿过主体的外壁并与冷却流体收集器和冷却流体腔连通; 与所述冷却流体腔连通的冷却流体出口; 以及从冷却流体出口通过主体外壁延伸的多个出口孔。

97. 发明申请

US20100239431A1 Turbine Airfoil Cooling System with Dual Serpentine Cooling Chambers 有权
标题翻译：具有双蛇形冷却室的涡轮翼型冷却系统
公开(公告)号：US20100239431A1
公开(公告)日：2010-09-23
申请号：US12407914
申请日：2009-03-20
申请人： George Liang
发明人： George Liang
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F05D2250/185 , F05D2260/205 , F05D2260/22141
摘要： A cooling system for a turbine airfoil of a turbine engine having dual serpentine cooling channels, an inward serpentine cooling channel and an outward serpentine cooling channel, positioned within the airfoil. The inward serpentine cooling channel may receive cooling fluids from a cooling supply system through the root and exhaust cooling fluids to the outward serpentine cooling channel at the leading edge. The outward serpentine cooling channel may pass the cooling fluids through the outward portion of the serpentine cooling channel and exhaust the cooling fluids through the trailing edge of the airfoil. Such configuration yields a better creep capability for the blade.
摘要翻译：一种用于涡轮发动机的涡轮机翼的冷却系统，其具有两个蛇形冷却通道，位于翼型内的向内的蛇形冷却通道和向外的蛇形冷却通道。向内的蛇形冷却通道可以将来自冷却供应系统的冷却流体通过根部和排出冷却流体接收到前缘的向外蛇形冷却通道。向外的蛇形冷却通道可以使冷却流体通过蛇形冷却通道的向外部分，并且通过翼型件的后缘排出冷却流体。这种构造为刀片产生更好的蠕变能力。

98. 发明申请

US20100226791A1 BLADE COOLING STRUCTURE OF GAS TURBINE 有权
标题翻译：气体涡轮叶片冷却结构
公开(公告)号：US20100226791A1
公开(公告)日：2010-09-09
申请号：US12670912
申请日：2007-08-30
申请人： Daigo Fujimura , Hideaki Sugishita , Masaaki Matsuura , Hiroyuki Yamamoto , Shunsuke Torii , Satoshi Hada , Kiyoshi Suenaga , Yuko Suenaga
发明人： Daigo Fujimura , Hideaki Sugishita , Masaaki Matsuura , Hiroyuki Yamamoto , Shunsuke Torii , Satoshi Hada , Kiyoshi Suenaga , Yuko Suenaga
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F05D2240/127 , F05D2250/185 , F05D2260/2212 , F05D2260/22141 , Y02T50/676
摘要： A blade cooling structure of a gas turbine, which can reduce the pressure loss of a cooling medium without decreasing the heat transfer coefficient, is provided. The blade cooling structure comprises a cooling passage (15) for flowing cooling air (A) from a proximal end portion (12) toward a blade portion (14) of a moving blade (11), a plurality of turbulators (21) arranged, on both wall surfaces of the cooling passage (15) opposing each other, in such a manner as to be inclined with respect to the flowing direction of the cooling air (A), and a plurality of dimples (22) formed in a downstream region (N) downstream of a center position (O) in the flowing direction of the cooling air (A) on the wall surface of the cooling passage (15) between the adjacent turbulators (21).
摘要翻译：提供了一种燃气轮机的叶片冷却结构，其可以在不降低传热系数的情况下降低冷却介质的压力损失。叶片冷却结构包括用于使冷却空气（A）从基端部（12）朝向活动叶片（11）的叶片部分（14）流动的冷却通道（15），多个湍流器（21）在相对于冷却空气（A）的流动方向倾斜的方式相互相对的冷却通路（15）的两壁面上形成有多个凹部（22），形成在下游区域（N）在冷却空气（A）的流动方向上在相邻的湍流器（21）之间的冷却通道（15）的壁表面上的中心位置（O）的下游。

99. 发明申请

US20100226788A1 TURBINE BLADE WITH INCREMENTAL SERPENTINE COOLING CHANNELS BENEATH A THERMAL SKIN 失效
标题翻译：涡轮叶片与增压塞尔温冷却通道BENEATH A热皮肤
公开(公告)号：US20100226788A1
公开(公告)日：2010-09-09
申请号：US12397766
申请日：2009-03-04
申请人： George Liang
发明人： George Liang
IPC分类号： F01D5/18
CPC分类号： F01D5/188 , F01D5/187 , F05D2250/185 , F05D2260/22141
摘要： A turbine blade having an internal cooling system with incremental serpentine cooling channels in near walls forming an outer surface of the turbine blade is disclosed. The turbine blade may be formed from an internal structural spar that is covered with a thermal skin. The incremental serpentine cooling channels may be cut into the outer surface of the spar to which the thermal skin may be attached. The incremental serpentine cooling channels may be formed from two or more serpentine cooling channels aligned along an axis that extends generally spanwise throughout the turbine blade. A row of incremental serpentine cooling channels may extend from a root to a tip of the blade, but a single incremental cooling channel does not.
摘要翻译：公开了一种具有内部冷却系统的涡轮机叶片，该内部冷却系统在形成涡轮机叶片的外表面的近壁处具有增量的蛇形冷却通道。涡轮机叶片可以由内部结构的翼梁形成，内部的结构翼梁被热的皮肤覆盖。增量蛇形冷却通道可以被切割到可以附着热皮肤的翼梁的外表面。增量蛇形冷却通道可以由两个或更多个沿着轴线对齐的蛇形冷却通道形成，该轴线大致跨越涡轮机叶片。一排增量蛇形冷却通道可以从根部延伸到刀片的尖端，但是单个增量冷却通道不会。

100. 发明申请

US20100226755A1 Turbine Vane for a Gas Turbine Engine Having Serpentine Cooling Channels Within the Outer Wall 有权
标题翻译：用于燃气轮机的涡轮叶片在外壁内具有蛇形冷却通道
公开(公告)号：US20100226755A1
公开(公告)日：2010-09-09
申请号：US12396660
申请日：2009-03-03
申请人： George Liang
发明人： George Liang
IPC分类号： F01D5/18 , F02C7/12
CPC分类号： F01D5/187 , F01D9/04 , F01D25/12 , F05D2240/128 , F05D2250/185 , F05D2260/202 , F05D2260/22141
摘要： A turbine vane for a gas turbine engine having an outer wall containing a plurality of serpentine cooling channels. The serpentine cooling channels may be configured to receive cooling fluids from internal cooling fluids supply channels. The serpentine cooling channels may be positioned in the pressure side and suction side outer walls and configured such that a first pass is positioned radially outward from an internal chamber a greater distance than a second pass. As such, cooling fluids are first passed proximate to an outer surface where the fluids are heated and then passed proximate to an inner surface, thereby establishing a smaller thermal gradient than typically found in conventional turbine blade outer walls.
摘要翻译：一种用于燃气涡轮发动机的涡轮叶片，其具有包含多个蛇形冷却通道的外壁。蛇形冷却通道可以被配置为从内部冷却流体供应通道接收冷却流体。蛇形冷却通道可以位于压力侧和吸入侧外壁中，并且构造成使得第一通路从内室径向向外定位，比第二通路更大的距离。因此，冷却流体首先通过附近流体被加热的外表面，然后靠近内表面通过，从而建立比常规涡轮机叶片外壁中典型的较小的热梯度。

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