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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：US20090238675A1
公开(公告)日：2009-09-24
申请号：US11520374
申请日：2006-09-13
IPC分类号： F04D29/58
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：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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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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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：US20080056909A1
公开(公告)日：2008-03-06
申请号：US11516143
申请日：2006-09-05
IPC分类号： F01D5/18
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：US20120045319A1
公开(公告)日：2012-02-23
申请号：US13283752
申请日：2011-10-28
CPC分类号： F01D25/30 , F02C7/18 , F02K1/822 , F05D2260/201 , F05D2260/202 , Y02T50/67 , Y02T50/676
摘要： A system comprises a bypass duct, a turbine case, a turbine exhaust ring and a splash plate. The turbine case is formed along a radially inner margin of the bypass duct, and the turbine exhaust ring is coaxially disposed within the turbine case. The splash plate extends axially along the turbine exhaust ring, radially spaced between the turbine exhaust ring and the turbine case. There are cooling fluid apertures in the turbine case to provide cooling fluid flow from the bypass duct onto the splash plate, and impingement holes in the splash plate to provide impingement flow onto the turbine exhaust ring.
摘要翻译： 一种系统包括旁通管道，涡轮机壳体，涡轮排气环和飞溅板。 涡轮壳体沿着旁通管道的径向内缘形成，并且涡轮机排气环同轴地设置在涡轮机壳体内。 飞溅板沿着涡轮机排气环轴向延伸，在涡轮机排气环和涡轮机壳之间径向间隔开。 在涡轮壳体中存在冷却流体孔，以提供从旁路管道到飞溅板的冷却流体流，以及飞溅板中的冲击孔，以在涡轮机排气环上提供冲击流。
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公开(公告)号：US20100247328A1
公开(公告)日：2010-09-30
申请号：US11447463
申请日：2006-06-06
申请人： Francisco J. Cunha
发明人： Francisco J. Cunha
IPC分类号： F01D5/18
CPC分类号： F01D5/186 , F05D2250/11 , F05D2250/121 , F05D2260/204 , F05D2260/2212 , Y02T50/676
摘要： A turbine engine component, such as a turbine blade, includes at least one cooling circuit having a plurality of legs through which a cooling fluid flows, and a plurality of cooling devices in at least one of the legs. Each of the cooling devices has a heat transfer multiplier in the range of from 1.8 to 2.4 and a reattachment length in the range of from 1.9 to 2.5.
摘要翻译： 诸如涡轮叶片的涡轮发动机部件包括至少一个冷却回路，该冷却回路具有冷却流体流经的多个支管，以及至少一个支腿中的多个冷却装置。 每个冷却装置具有在1.8至2.4范围内的传热倍增器，并且重新附着长度在1.9至2.5的范围内。
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公开(公告)号：US07722325B2
公开(公告)日：2010-05-25
申请号：US11594263
申请日：2006-11-08
申请人： Francisco J. Cunha
发明人： Francisco J. Cunha
IPC分类号： F01D5/18
CPC分类号： F01D5/186 , F01D5/187 , F05D2260/202 , F05D2260/2212 , Y02T50/67 , Y02T50/673 , Y02T50/676
摘要： An article, such as a gas turbine engine turbine blade, includes a film cooling system having a trench recessed within a wall of the component, a passage that opens into the trench for discharging a coolant flow into the trench, and a guide member within the trench for influencing the coolant flow discharge from the passage.
摘要翻译： 诸如燃气涡轮发动机涡轮机叶片的物品包括薄膜冷却系统，该薄膜冷却系统具有在组件的壁内凹陷的凹槽，通向沟槽中的通道，用于将冷却剂流排放到沟槽中，以及引导构件 用于影响从通道排出的冷却剂流的沟槽。
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公开(公告)号：US07581928B1
公开(公告)日：2009-09-01
申请号：US11494831
申请日：2006-07-28
申请人： Francisco J. Cunha
发明人： Francisco J. Cunha
CPC分类号： F01D5/187 , F05D2260/221
摘要： A turbine engine component, such as a turbine blade, has an airfoil portion with a pressure side and a suction side. The turbine engine component also has a first cooling circuit within the pressure side for cooling the pressure side of the airfoil portion and a second cooling circuit within the suction side for cooling the suction side of the airfoil portion and for cooperating with a wrap around leading edge cooling circuit for creating a cooling film over the pressure side.
摘要翻译： 诸如涡轮叶片的涡轮发动机部件具有具有压力侧和吸力侧的翼型部分。 涡轮发动机部件还具有在压力侧内的用于冷却翼型部分的压力侧的第一冷却回路和吸入侧内的第二冷却回路，用于冷却翼型部分的吸入侧，并且与前缘 用于在压力侧产生冷却膜的冷却回路。
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