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公开(公告)号：US06254345B1
公开(公告)日：2001-07-03
申请号：US09390993
申请日：1999-09-07
IPC分类号： F01D518
CPC分类号： F01D5/18 , F01D5/225 , F05D2260/20 , Y02T50/671 , Y02T50/676
摘要： A gas turbine engine turbine blade shrouded tip has an airfoil tip with a cross-sectional airfoil shape, a blade tip shroud attached to the tip, and a shroud cooling circuit disposed within the blade tip shroud. The shroud cooling circuit is operable for cooling substantially all of the shroud and is in fluid communication with a hollow interior of the tip. One embodiment of the invention includes two circumferentially extending forward and aft seal teeth on a radially outer shroud surface of the shroud extending in a radial direction away from the hollow interior of the tip. The shroud cooling circuit includes circumferentially extending shroud cooling passages between clockwise and counter-clockwise shroud side edges of the shroud. Forward and aft pluralities of the shroud cooling passages within the tip shroud are in fluid communication with first and second cavities respectively in the hollow interior.
摘要翻译： 燃气涡轮发动机涡轮机叶片被覆盖的末端具有翼形翼片，其具有横截面翼型形状，附接到尖端的叶片梢罩，以及设置在叶片梢罩内的护罩冷却回路。 护罩冷却回路可操作用于冷却基本上所有护罩，并且与顶端的中空内部流体连通。 本发明的一个实施例包括在护罩的径向外护罩表面上的两个沿周向延伸的前后密封齿，其径向方向远离尖端的中空内部。 护罩冷却回路包括在护罩的顺时针和逆时针护罩侧边缘之间的周向延伸的护罩冷却通道。 前端和后端尖端护罩内的多个护罩冷却通道分别与中空内部的第一和第二空腔流体连通。
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公开(公告)号：US06224337B1
公开(公告)日：2001-05-01
申请号：US09399195
申请日：1999-09-17
IPC分类号： F01D518
CPC分类号： F01D5/20 , C23C4/01 , F01D5/18 , F01D5/288 , F05D2230/90 , F05D2300/2118 , F05D2300/502
摘要： A turbine blade squealer tip includes an airfoil shaped tip cap having a squealer tip wall extending radially outwardly from and around the perimeter of the airfoil shaped tip cap to define a radially outwardly open tip cavity. The tip wall has an inboard side facing the interior of the cavity and an outboard side facing away from the cavity and the tip cap has an outer tip side on a bottom of the cavity. Thermal barrier coatings are disposed on the inboard and outboard sides of the squealer tip wall and on the outer tip side of the tip cap. One embodiment provides the tip cap with cooling holes disposed therethrough to flow cooling air into the cavity.
摘要翻译： 涡轮叶片尖叫尖端包括具有从翼型形状的顶盖的周边的周向径向向外延伸以形成径向向外敞开的尖端腔的尖端顶端壁的翼型形尖端帽。 尖端壁具有面向空腔内部的内侧面和背离空腔的外侧面，并且顶盖具有位于空腔底部的外侧末端侧。 热障涂层设置在尖叫尖端壁的内侧和外侧以及尖端盖的外侧末端侧。 一个实施例提供了顶盖，其具有穿过其设置的冷却孔，以将冷却空气流入空腔。
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公开(公告)号：US06224336B1
公开(公告)日：2001-05-01
申请号：US09328470
申请日：1999-06-09
申请人： David M. Kercher
发明人： David M. Kercher
IPC分类号： F01D518
摘要： A turbine airfoil includes pressure and suction sidewalls extending between leading and trailing edges and from root to tip. The tip includes a floor bounding an internal cooling channel within the airfoil which channels cooling air. The airfoil tip includes a first rib adjacent the pressure sidewall, a second rib spaced therefrom to define a first slot, and a third rib adjacent the suction sidewall to define a second slot with the second rib. The tip floor includes feed holes extending between the cooling channel and the first slot for supplying cooling air therein for discharge over the second rib towards the third rib.
摘要翻译： 涡轮机翼片包括在前缘和后缘之间从根部到尖端延伸的压力和吸力侧壁。 尖端包括限定翼型内部的内部冷却通道的底板，其通过冷却空气。 翼型件末端包括邻近压力侧壁的第一肋，与其间隔开的第二肋，以限定第一槽，以及与吸力侧壁相邻以限定具有第二肋的第二槽的第三肋。 尖端地板包括在冷却通道和第一槽之间延伸的进料孔，用于在其中供应冷却空气，以在第二肋条上向第三肋排放。
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公开(公告)号：US06217279B1
公开(公告)日：2001-04-17
申请号：US09230820
申请日：1999-02-10
申请人： Toshishige Ai , Masanori Yuri , Yasuoki Tomita , Kiyoshi Suenaga , Sunao Aoki , Hiroki Fukuno
发明人： Toshishige Ai , Masanori Yuri , Yasuoki Tomita , Kiyoshi Suenaga , Sunao Aoki , Hiroki Fukuno
IPC分类号： F01D518
CPC分类号： F01D9/065 , F01D11/001 , F02C7/18
摘要： A sealing device for a gas turbine stator blade, in which an outer shroud (32) is mounted by heat insulating rings (32a,32b) on a blade ring (50). The blade ring (50) has a first air hole (1), which communicates with a space (53), and a second air hole (51), which communicates with a seal tube (2). The seal tube (2) is inserted into the second air hole (51), and a spring (6) is arranged between a projection (4) of the tube (2) and a retaining portion (5) of the air hole (51) to removably secure the seal tube (2). Cooling air (54) flows through the first air hole (1) to cool the shrouds and the inside of a stator blade (31) until it is released from the trailing edge of the blade. The cooling air also flows into a cavity (36) so that a high pressure can be maintained without a pressure loss because the tube (2) is independent of the space (53) in the blade ring.
摘要翻译： 一种用于燃气轮机定子叶片的密封装置，其中外护罩（32）通过隔离环（32a，32b）安装在叶片环（50）上。 叶片环（50）具有与空间（53）连通的第一空气孔（1）和与密封管（2）连通的第二空气孔（51）。 密封管（2）插入到第二空气孔（51）中，弹簧（6）布置在管（2）的突出部（4）和气孔（51）的保持部分（5）之间 ）以可拆卸地固定密封管（2）。 冷却空气（54）流过第一空气孔（1）以冷却护罩和定子叶片（31）的内部，直到其从叶片的后缘释放。 冷却空气也流入空腔（36），从而由于管（2）独立于叶片环中的空间（53）而能够保持高压而没有压力损失。
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公开(公告)号：US06196799B1
公开(公告)日：2001-03-06
申请号：US09252064
申请日：1999-02-18
申请人： Ichiro Fukue , Eiji Akita , Kiyoshi Suenaga , Yasuoki Tomita , Koji Watanabe
发明人： Ichiro Fukue , Eiji Akita , Kiyoshi Suenaga , Yasuoki Tomita , Koji Watanabe
IPC分类号： F01D518
CPC分类号： F01D5/187 , F01D5/186 , F05D2240/81
摘要： A gas turbine moving blade platform having a simplified cooling structure for effecting uniform cooling of the platform. The platform (1) includes cavities (2, 3, 4) and an impingement plate (11) provided below the cavities (2, 3, 4). A cooling hole (5) communicates with cavity (2), cooling hole (6) communicated with cavity (3) and cooling holes (7, 8) communicate with cavity (4) and all of the cooling holes pass through the platform (1) at an inclined angle. Cooling air (70) flows into the cavities (2, 3, 4) through holes (12) in the impingement plate (11) for effecting impingement cooling of platform (1) plane portion. The cooling air (70) further flows through the cooling holes (5, 6, 7) to blow outside angularly upward for cooling peripheral portions of the platform. Thus, the platform is cooled uniformly, no lengthy and complicated cooling passage is provided, and workability is enhanced.
摘要翻译： 一种具有简化冷却结构的燃气轮机动叶片平台，用于实现平台的均匀冷却。 平台（1）包括空腔（2,3,4）和设置在空腔（2,3,4）下方的冲击板）。 冷却孔（5）与空腔（2）连通，与空腔（3）连通的冷却孔（6）和冷却孔（7,8）与空腔（4）连通，所有的冷却孔都通过平台 ）。 冷却空气（70）通过冲击板（11）中的孔（12）流入空腔（2,3,4），以实现平台（1）平面部分的冲击冷却。 冷却空气（70）进一步流过冷却孔（5,6,7）以向外侧向外侧吹出以冷却平台的周边部分。 因此，平台被均匀地冷却，没有设置冗长且复杂的冷却通道，并且可加工性得到提高。
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公开(公告)号：US06186740B1
公开(公告)日：2001-02-13
申请号：US09035217
申请日：1998-03-05
IPC分类号： F01D518
CPC分类号： F01D5/189 , F05D2260/201 , F05D2260/202 , Y02E20/16
摘要： In a gas turbine cooling blade, cooling passages are defined by ribs formed therein. The cooling blade comprises an insert fitted in one of the cooling passages at the front edge of the blade, a plurality of nozzles formed in the front face of the insert and used to spray an impact jet of a refrigerant against the inner surface of the front edge of the blade, thereby cooling the inner surface, and a passage formed between the rear face of the insert and the rib and communicating with a rear-side flow.
摘要翻译： 在燃气轮机冷却叶片中，冷却通道由其中形成的肋限定。 冷却叶片包括嵌入在叶片前缘的一个冷却通道中的插入件，形成在插入件的前表面中的多个喷嘴，用于将制冷剂的冲击射流喷射到前部的内表面上 从而冷却内表面，以及形成在插入件的后表面和肋之间并与后侧流连通的通道。
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公开(公告)号：US06183198B2
公开(公告)日：2001-02-06
申请号：US09192229
申请日：1998-11-16
IPC分类号： F01D518
CPC分类号： F01D5/186 , F05D2260/201 , F05D2260/202
摘要： A gas turbine engine airfoil includes first and second sidewalls joined together at opposite leading and trailing edges, and spaced apart from each other therebetween to define a leading edge channel extending longitudinally from a root to a tip of the airfoil. A plurality of film cooling holes extend through the leading edge and are disposed in flow communication with the leading edge channel. An isolation plenum extends along the first sidewall and adjacent the leading edge channel, and is separated therefrom by a partition having a plurality of inlet holes. A plurality of film cooling gill holes extend through the first sidewall, and are disposed in flow communication with the isolation plenum. Cooling air is channeled from the leading edge channel to the isolation plenum for feeding the gill holes with reduced pressure air.
摘要翻译： 燃气涡轮发动机翼型件包括在相对的前缘和后缘处连接在一起并且彼此间隔开的第一和第二侧壁，以限定从叶片纵向延伸到翼型的尖端的前缘通道。 多个膜冷却孔延伸穿过前缘并且与前缘通道流体连通地设置。 隔离通风室沿着第一侧壁延伸并且邻近前缘通道，并且通过具有多个入口孔的隔板与其隔开。 多个薄膜冷却鳃孔延伸穿过第一侧壁，并且与隔离气室成流动连通地设置。 冷却空气从前缘通道引导到隔离气室，用于通过减压空气供给鳃孔。
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58.发明授权公开(公告)号：US06168380A
公开(公告)日：2001-01-02
申请号：US09111874
申请日：1998-07-08
申请人： Bernhard Weigand
发明人： Bernhard Weigand
IPC分类号： F01D518
CPC分类号： F01D5/187
摘要： In a cooling system for the leading-edge region of a hollow gas-turbine blade, a duct (10) extends inside the thickened blade leading edge (5) from the blade root (1) up to the blade tip (2). The duct (10), via a plurality of bores (9) made in the blade leading edge, communicates with a main duct (3), through which the cooling medium flows longitudinally, and the flow through the duct (10) occurs longitudinally over the blade height, and the duct (10) is formed with a variable cross section. The cross section of the duct (10) increases continuously in the direction of flow of the cooling medium from the blade root up to the blade tip. In the case of blades having a cover plate (11), the duct (10) merges at its top end into a chamber (12), which is mounted below the cover plate and is in operative connection with a pressure source, the pressure of which is lower than the pressure in the main duct.
摘要翻译： 在用于中空燃气涡轮机叶片的前缘区域的冷却系统中，管道（10）在增厚的叶片前缘（5）内部从叶片根部（1）延伸到叶片尖端（2）。 管道（10）通过在叶片前缘中制成的多个孔（9）与主管道（3）连通，冷却介质通过该主管道纵向流动，并且通过管道（10）的流动纵向地发生在 刀片高度和管道（10）形成有可变截面。 管道（10）的横截面在冷却介质从叶片根部到叶片尖端的流动方向上连续增加。 在具有盖板（11）的叶片的情况下，管道（10）在其顶端处汇合到室（12）中，室（12）安装在盖板下方并与压力源操作连接， 其低于主管道中的压力。
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59.发明授权公开(公告)号：US06817833B2
公开(公告)日：2004-11-16
申请号：US10231187
申请日：2002-08-30
申请人： Frank Haselbach
发明人： Frank Haselbach
IPC分类号： F01D518
CPC分类号： F01D5/186 , Y02T50/673 , Y02T50/676
摘要： The invention relates to a turbine blade of a gas turbine with at least one cooling excavation 2 which connects an interior 3 and the surface 4 of the turbine blade 1, characterized in that a mouth 5 of the cooling excavation 2 is provided with a protrusion 6 in its downstream area.
摘要翻译： 本发明涉及一种具有至少一个连接内部3和涡轮叶片1的表面4的冷却挖掘2的燃气轮机的涡轮机叶片，其特征在于，冷却挖掘机构2的口部5设置有突起6 在其下游地区。
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公开(公告)号：US06814544B2
公开(公告)日：2004-11-09
申请号：US10228103
申请日：2002-08-27
IPC分类号： F01D518
CPC分类号： B23K11/02 , B23K2101/001 , Y10T29/49318
摘要： In a joining method for manufacturing a rotor blade by joining a plurality of members, the members are pressed so as to exert a predetermined pressure on the bonding interface. A pulse voltage is applied to the members to pass electric current therethrough, and the joint portion is heated by resistance heating generated at the bonding interface and in the bulk of the members to cause diffusion bonding and thereby to join the members to each other. With this method, good joining can be achieved without substantially changing the crystal structure and mechanical properties of the base metals.
摘要翻译： 在通过接合多个构件来制造转子叶片的接合方法中，将构件按压以在接合界面上施加预定压力。 向构件施加脉冲电压以使电流通过，并且通过在接合界面和大部分构件中产生的电阻加热来加热接合部分，从而引起扩散接合，从而使构件彼此接合。 通过这种方法，可以实现良好的接合，而基本上不改变贱金属的晶体结构和机械性能。
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