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公开(公告)号：US07625179B2
公开(公告)日：2009-12-01
申请号：US11520374
申请日：2006-09-13
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F05D2260/2214
摘要： A turbine engine component, such as a turbine engine blade, has an airfoil portion with a pressure side wall and a suction side wall, a plurality of ribs extending between the pressure side wall and the suction side wall, and a plurality of supply cavities located between the ribs. The component further has an arrangement for cooling the airfoil portion. The cooling arrangement comprises a first cooling circuit embedded within the suction side wall for convectively cooling the suction side wall, a second cooling circuit embedded within the pressure side wall for cooling the pressure side wall, and a third passageway for increasing a temperature of at least one of the ribs by conduction.
摘要翻译： 诸如涡轮发动机叶片的涡轮发动机部件具有翼型部分，其具有压力侧壁和吸力侧壁，在压力侧壁和吸力侧壁之间延伸的多个肋，以及多个供应腔， 在肋骨之间。 该部件还具有用于冷却翼型部的布置。 冷却装置包括嵌入在吸入侧壁内的第一冷却回路，用于对流冷却吸入侧壁，嵌入在压力侧壁内的用于冷却压力侧壁的第二冷却回路，以及用于增加至少温度的第三通道 肋骨之一通过传导。
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公开(公告)号：US20090238694A1
公开(公告)日：2009-09-24
申请号：US11495131
申请日：2006-07-28
申请人： Francisco J. Cunha
发明人： Francisco J. Cunha
IPC分类号： F01D5/18
CPC分类号： F01D5/188 , F01D5/186 , F01D5/187 , F05D2250/185 , F05D2260/202
摘要： A turbine engine component, such as a turbine blade has an airfoil portion with an airfoil mean line, a pressure side, and a suction side. A first region on the pressure side of the airfoil portion has a first array of cooling microcircuits embedded in a wall forming the pressure side. A second region on the pressure side has a second array of cooling microcircuits embedded in the wall. The first region is located on a first side of the mean line and the second region is located on a second side of the mean line.
摘要翻译： 诸如涡轮叶片的涡轮发动机部件具有具有翼型平均线，压力侧和吸力侧的翼型部分。 在翼型部分的压力侧的第一区域具有嵌入形成压力侧的壁中的冷却微电路的第一阵列。 压力侧的第二区域具有嵌入在壁中的第二阵列的冷却微电路。 第一区域位于平均线的第一侧，第二区域位于平均线的第二侧。
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公开(公告)号：US20080019839A1
公开(公告)日：2008-01-24
申请号：US11489155
申请日：2006-07-18
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F05D2250/185 , F05D2260/202
摘要： A turbine engine component has an airfoil portion having a pressure side, a suction side, a leading edge, a trailing edge, and a tip. The component further has a first cooling microcircuit embedded in a pressure side wall, a second cooling microcircuit embedded in a suction side wall, and a system for cooling the tip comprising a first tip cooling microcircuit receiving cooling fluid from the first cooling microcircuit and a second tip cooling microcircuit receiving cooling fluid from the second cooling microcircuit.
摘要翻译： 涡轮发动机部件具有具有压力侧，吸力侧，前缘，后缘和末端的翼型部。 该组件还具有嵌入在压力侧壁中的第一冷却微电路，嵌入在吸入侧壁中的第二冷却微电路，以及用于冷却尖端的系统，包括从第一冷却微电路接收冷却流体的第一末端冷却微电路和第二冷却微电路 尖端冷却微电路从第二冷却微电路接收冷却流体。
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公开(公告)号：US5320483A
公开(公告)日：1994-06-14
申请号：US996931
申请日：1992-12-30
申请人： Francisco J. Cunha , R. Paul Chiu
发明人： Francisco J. Cunha , R. Paul Chiu
CPC分类号： F01D5/187 , F02C7/18 , F05D2240/81 , F05D2260/201 , F05D2260/202 , F05D2260/2212 , F05D2260/2322
摘要： The second-stage nozzles include a plurality of stator vanes 10 having first, second, third, fourth and fifth passages 40, 42, 44, 46 and 48, respectively, for cooling the vanes. The first and fourth passages have a steam inlet along an outer sidewall 14 and a junction box 70 along the inner sidewall 12 for returning steam to the second passage 42. The third passage 44 has a contour corresponding to the contour of the leading edge and impingement steam is directed through openings in a partition 52, cooling the leading edge. Steam flows from the third passage 44 directly into the return passage 42 and also into a channel 64 for cooling the inner sidewall 12. Cooling air flows through fifth passage 48 radially inwardly through the inner sidewall 12 into a cavity 72 in the diaphragm 32 for flow axially outwardly into wheel cavities 86 and 88.
摘要翻译： 第二级喷嘴包括分别具有用于冷却叶片的第一，第二，第三，第四和第五通道40,42,44,46和48的多个定子叶片10。 第一和第四通道具有沿着外侧壁14的蒸汽入口和沿着内侧壁12的接线盒70，用于将蒸汽返回到第二通道42.第三通道44具有对应于前缘和冲击的轮廓的轮廓 蒸汽通过分隔件52中的开口引导，冷却前缘。 蒸汽从第三通道44直接流入返回通道42并且还流入用于冷却内侧壁12的通道64.冷却空气流经第五通道48径向向内通过内侧壁12进入隔膜32中的空腔72以用于流动 轴向向外进入轮腔86和88。
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25.发明授权公开(公告)号：US07980822B2
公开(公告)日：2011-07-19
申请号：US12708708
申请日：2010-02-19
IPC分类号： F01D5/08
CPC分类号： F01D5/187 , F05D2250/185
摘要： A cooling arrangement for a pressure side of an airfoil portion of a turbine engine component is provided. The cooling arrangement comprises a pair of cooling circuits embedded within a wall forming the pressure side. The pair of cooling circuits includes a first serpentine cooling circuit and a second circuit offset from the first serpentine cooling circuit.
摘要翻译： 提供了一种用于涡轮发动机部件的翼型部分的压力侧的冷却装置。 冷却装置包括嵌入在形成压力侧的壁内的一对冷却回路。 该对冷却回路包括第一蛇形冷却回路和偏离第一蛇形冷却回路的第二回路。
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26.发明申请公开(公告)号：US20100150735A1
公开(公告)日：2010-06-17
申请号：US12708708
申请日：2010-02-19
IPC分类号： F02C7/12
CPC分类号： F01D5/187 , F05D2250/185
摘要： A cooling arrangement for a pressure side of an airfoil portion of a turbine engine component is provided. The cooling arrangement comprises a pair of cooling circuits embedded within a wall forming the pressure side. The pair of cooling circuits includes a first serpentine cooling circuit and a second circuit offset from the first serpentine cooling circuit.
摘要翻译： 提供了一种用于涡轮发动机部件的翼型部分的压力侧的冷却装置。 冷却装置包括嵌入在形成压力侧的壁内的一对冷却回路。 该对冷却回路包括第一蛇形冷却回路和偏离第一蛇形冷却回路的第二回路。
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27.发明授权公开(公告)号：US07722324B2
公开(公告)日：2010-05-25
申请号：US11516143
申请日：2006-09-05
IPC分类号： F01D5/08
CPC分类号： F01D5/187 , F05D2250/185
摘要： A cooling arrangement for a pressure side of an airfoil portion of a turbine engine component is provided. The cooling arrangement comprises a pair of cooling circuits embedded within a wall forming the pressure side. The pair of cooling circuits includes a first serpentine cooling circuit and a second circuit offset from the first serpentine cooling circuit.
摘要翻译： 提供了一种用于涡轮发动机部件的翼型部分的压力侧的冷却装置。 冷却装置包括嵌入在形成压力侧的壁内的一对冷却回路。 该对冷却回路包括第一蛇形冷却回路和偏离第一蛇形冷却回路的第二回路。
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公开(公告)号：US07607890B2
公开(公告)日：2009-10-27
申请号：US11449521
申请日：2006-06-07
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F05D2260/2214
摘要： A cooling microcircuit for use in a turbine engine component, such as a turbine blade, having an airfoil portion is provided. The cooling microcircuit has at least one inlet slot for introducing a flow of coolant into the cooling microcircuit, a plurality of fluid exit slots for distributing a film of the coolant over the airfoil portion, and structures for substantially preventing one jet of the coolant exiting through one of the fluid exit slots from overpowering a second jet of the coolant exiting through the one fluid exit slot.
摘要翻译： 提供了用于具有翼型部分的涡轮发动机部件（例如涡轮机叶片）中的冷却微型电路。 冷却微电路具有用于将冷却剂流引入冷却微电路的至少一个入口槽，用于将冷却剂的膜分配在翼型部分上的多个流体出口槽，以及用于基本上防止冷却剂流出的一个射流的结构 其中一个流体出口插槽超过通过一个流体出口槽排出的冷却剂的第二射流。
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公开(公告)号：US20090028703A1
公开(公告)日：2009-01-29
申请号：US11881585
申请日：2007-07-27
IPC分类号： F01D5/18
CPC分类号： F01D5/186 , F01D5/187 , F01D25/32 , F05D2260/204 , F05D2260/607 , Y10T29/49341
摘要： A turbine engine component, such as a high pressure turbine vane, has an airfoil portion and at least one coolant system embedded within the airfoil portion. Each coolant system has an exit through which a cooling fluid flows, which exit has at least one device for preventing deposits from interfering with the flow of cooling fluid from the exit. The at least one device may be at least one depression and/or at least one grill structure formed from elongated ribs.
摘要翻译： 诸如高压涡轮叶片的涡轮发动机部件具有翼型部分和嵌入在翼型部分内的至少一个冷却剂系统。 每个冷却剂系统具有冷却流体流过的出口，该出口具有至少一个用于防止沉积物干扰来自出口的冷却流体流动的装置。 至少一个装置可以是由细长肋形成的至少一个凹陷部和/或至少一个格栅结构。
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公开(公告)号：US07413403B2
公开(公告)日：2008-08-19
申请号：US11317394
申请日：2005-12-22
IPC分类号： F01D5/08
CPC分类号： F01D5/187 , B22C9/10 , B22C9/103 , F01D5/186 , F01D5/20 , F05D2230/21 , F05D2230/80 , F05D2260/202
摘要： A turbine engine blade has an attachment root, a platform outboard of the attachment root, and an airfoil extending from the platform. The airfoil has pressure and suction sides extending between leading and trailing edges. An internal cooling passageway network includes at least one inlet in the root and a plurality of outlets along the airfoil. The passageway network includes a leading spanwise cavity fed by a first trunk. A streamwise cavity is inboard of a tip of the airfoil. A spanwise feed cavity feeds the streamwise cavity absent down-pass. A second trunk feeds the spanwise feed cavity.
摘要翻译： 涡轮发动机叶片具有附件根部，附件根部外侧的平台以及从平台延伸的翼型件。 翼型件具有在前缘和后缘之间延伸的压力和吸力侧。 内部冷却通道网络包括根部中的至少一个入口和沿翼型的多个出口。 通道网络包括由第一干线供给的前导翼展空腔。 流体腔位于机翼末端的内侧。 翼展式进料腔进料流槽不存在下通道。 第二个干线供应翼展向进料腔。
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