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51. 发明授权

US06315518B1 Stationary blade of gas turbine 有权
标题翻译：燃气轮机固定叶片
公开(公告)号：US06315518B1
公开(公告)日：2001-11-13
申请号：US09230751
申请日：1999-02-01
申请人： Kazuo Uematsu , Kiyoshi Suenaga
发明人： Kazuo Uematsu , Kiyoshi Suenaga
IPC分类号： F01D518
CPC分类号： F02C7/16 , F01D5/186 , F01D5/187 , F01D11/04 , F05D2240/81 , F05D2260/201 , F05D2260/205 , F05D2260/2212 , F05D2260/22141 , F05D2260/2322
摘要： In a stationary blade of a gas turbine, the pressure resisting strength can be decreased by using low-pressure cooling air, and effective cooling can be performed by means of a simple construction. An inside shroud 1 and an outside shroud 2 are cooled by cooling air passing through an impingement plate. A trailing edge portion of a blade portion 6, which is thin in shape, is cooled by cooling air flowing in an air passage 10. Part of this air is discharged through a hole 12 on the side of the inside shroud 1 as inside seal air for a combustion gas passage.
摘要翻译：在燃气轮机的固定叶片中，可以通过使用低压冷却空气来降低耐压强度，并且可以通过简单的结构进行有效的冷却。内部护罩1和外部护罩2由通过冲击板的冷却空气冷却。叶片部分6的后缘部分的形状很薄，由在空气通道10中流动的冷却空气冷却。这种空气的一部分通过作为内部密封空气的内侧护罩1侧的孔12排出用于燃烧气体通道。

52. 发明授权

US06264426B1 Gas turbine stationary blade 失效
标题翻译：燃气轮机固定叶片
公开(公告)号：US06264426B1
公开(公告)日：2001-07-24
申请号：US09026643
申请日：1998-02-20
申请人： Hiroki Fukuno , Yasuoki Tomita , Kiyoshi Suenaga
发明人： Hiroki Fukuno , Yasuoki Tomita , Kiyoshi Suenaga
IPC分类号： F01D518
CPC分类号： F01D5/187 , F05D2240/81 , F05D2260/201 , F05D2260/202 , F05D2260/2212 , F05D2260/2322
摘要： In cooling a gas turbine stationary blade, steam and air are used as cooling media, the steam is recovered surely without leakage and used effectively, and the amount of air required for cooling is decreased to provide a margin for combustion air, by which the gas turbine efficiency is improved. A steam cooling section is provided at the rear from the blade leading edge, and an air cooling section is provided at the blade trailing edge. The steam cooling is effected by cooling the blade by the cooling steam flowing in the serpentine flow path having turbulators after impingement cooling of an outside shroud and by impingement-cooling an inside shroud during the cooling process, the cooling steam being led to a recovery section from the outside shroud. On the other hand, the air cooling section consists of an air flow path extending from the outside shroud to the inside shroud and slot cooling at the blade trailing edge. Thus, the stationary blade is cooled by both of the steam cooling section and air cooling section.
摘要翻译：在冷却燃气轮机固定叶片时，蒸汽和空气被用作冷却介质，蒸汽被确保地回收而没有泄漏并被有效地使用，并且减少冷却所需的空气量以提供燃烧空气的余量，由此气体提高了涡轮效率。在叶片前缘的后部设有蒸汽冷却部，在叶片后缘设有空气冷却部。蒸汽冷却通过在具有湍流器的蛇形流动路径中流动的冷却蒸汽在外部护罩的冲击冷却之后冷却叶片并且在冷却过程中通过冲击冷却内部护罩来实现，冷却蒸汽被引导到回收部分从外面的围墙。另一方面，空气冷却部由从外侧护罩延伸到内部护罩的气流路径和在叶片后缘的冷却槽构成。因此，固定叶片由蒸汽冷却部分和空气冷却部分两者冷却。

53. 发明授权

US06196799B1 Gas turbine moving blade platform 失效
标题翻译：燃气轮机动叶片平台
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。

54. 发明授权

US06190128B1 Cooled moving blade for gas turbine 有权
标题翻译：燃气轮机的冷却动叶片
公开(公告)号：US06190128B1
公开(公告)日：2001-02-20
申请号：US09230942
申请日：1999-02-04
申请人： Hiroki Fukuno , Yasuoki Tomita , Shigeyuki Maeda , Yukihiro Hashimoto , Kiyoshi Suenaga
发明人： Hiroki Fukuno , Yasuoki Tomita , Shigeyuki Maeda , Yukihiro Hashimoto , Kiyoshi Suenaga
IPC分类号： F01D508
CPC分类号： F01D5/147 , F01D5/141 , F01D5/18 , F01D5/187 , F01D5/28 , F05D2240/80
摘要： A cooled moving blade for a gas turbine which has a blade profile capable of more effectively reducing thermal stress in a blade base portion and, thus, preventing cracks from occurring. A moving blade (1) is fixedly secured to a platform (2). On the other hand, a cooling air passage (3) is formed in a serpentine pattern inside of the blade for cooling with cooling air. The moving blade (1) has a base portion of a profile formed by an elliptically curved surface (11) and a rectilinear surface portion (12), wherein the rectilinear surface portion (12) is provided at a hub portion of the blade where thermal stress is large. The cross-sectional area of the blade is increased by providing the rectilinear surface portion (12) The heat capacity is increased, compared with the conventional blade, due to the increased cross-sectional area of the blade. This, in turn, results in a decrease of the temperature difference due to the thermal stress. Thus, the thermal stress can be suppressed more effectively than with the conventional blade.
摘要翻译：一种用于燃气轮机的冷却的移动叶片，其具有能够更有效地降低叶片基部中的热应力并因此防止裂纹发生的叶片轮廓。活动叶片（1）固定地固定到平台（2）上。另一方面，冷却空气通路（3）形成为叶片内的蛇形图案，用冷却空气冷却。活动叶片（1）具有由椭圆曲面（11）和直线表面部分（12）形成的轮廓的基部，其中直线表面部分（12）设置在叶片的毂部，其中热压力很大通过提供直线表面部分（12）来提高叶片的横截面面积。与常规叶片相比，由于叶片的横截面面积增加，热容量增加。这又导致由于热应力引起的温度差的降低。因此，与常规叶片相比，可以更有效地抑制热应力。

55. 发明授权

US06189891B1 Gas turbine seal apparatus 失效
标题翻译：燃气轮机密封装置
公开(公告)号：US06189891B1
公开(公告)日：2001-02-20
申请号：US09028664
申请日：1998-02-24
申请人： Yasuoki Tomita , Kazuharu Hirokawa , Hiroki Fukuno , Kiyoshi Suenaga , Yukihiro Hashimoto , Eisaku Ito
发明人： Yasuoki Tomita , Kazuharu Hirokawa , Hiroki Fukuno , Kiyoshi Suenaga , Yukihiro Hashimoto , Eisaku Ito
IPC分类号： F16J15447
CPC分类号： F01D11/02 , F01D11/001
摘要： A gas turbine seal structure provided between end portions of a moving blade platform and a stationary blade inside shroud. The sealing performance of the seal structure is improved by increasing the resistance to the flow of air. A seal plate (21, 31) is mounted to an end portion of a platform (2, 2′) of the moving blade (1) and a seal portion is formed by seal fins (22, 32) and a honeycomb seal (16, 17) disposed on a lower surface of an end portion (12a, 12b) of an inside shroud (12) of a stationary blade (11). Sealing air from the stationary blade (11) produces a high temperature in a cavity (14) and flows into a space (18, 19), and also air leaking from the cooling air of the moving blade (1) is able to escape into a high temperature combustion gas passage through a seal portion. However, since the seal plate has three seal fins (22, 32) that are inclined in a direction so as to oppose the air flow, air resistance is increased and the flow of air into the combustion gas passage is prevented.
摘要翻译：一种燃气轮机密封结构，其设置在活动叶片平台的端部和固定叶片内部的护罩内。通过增加对空气流动的阻力来改善密封结构的密封性能。密封板（21,31）安装在活动叶片（1）的平台（2,2'）的端部，密封部分由密封翅片（22,32）和蜂窝密封件（16）形成，17），其设置在固定叶片（11）的内侧护罩（12）的端部（12a，12b）的下表面上。来自固定叶片（11）的密封空气在空腔（14）中产生高温并流入空间（18,19），并且从活动叶片（1）的冷却空气泄漏的空气也能够逸出通过密封部分的高温燃烧气体通道。然而，由于密封板具有在与空气流相对的方向上倾斜的三个密封翅片（22,32），因此空气阻力增加，并且防止了进入燃烧气体通道的空气流。

56. 发明授权

US06186740B1 Gas turbine cooling blade 失效
标题翻译：燃气轮机冷却叶片
公开(公告)号：US06186740B1
公开(公告)日：2001-02-13
申请号：US09035217
申请日：1998-03-05
申请人： Kenichiro Takeishi , Kiyoshi Suenaga , Kazuo Uematsu
发明人： Kenichiro Takeishi , Kiyoshi Suenaga , Kazuo Uematsu
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。

57. 发明授权

US6146091A Gas turbine cooling structure 有权
标题翻译：燃气轮机冷却结构
公开(公告)号：US6146091A
公开(公告)日：2000-11-14
申请号：US256102
申请日：1999-02-24
申请人： Koji Watanabe , Akiko Aizawa , Rintaro Chikami , Kiyoshi Suenaga
发明人： Koji Watanabe , Akiko Aizawa , Rintaro Chikami , Kiyoshi Suenaga
IPC分类号： F01D9/04 , F01D11/04 , F01D11/10 , F01D11/24 , F01D25/12 , F01D9/02 , F01D9/06
CPC分类号： F01D9/041 , F01D11/04 , F01D11/10 , F01D11/24 , F01D25/12 , F01D9/04 , Y02T50/675
摘要： A gas turbine having cooling structure disposed on an outside peripheral side in a radial direction of a movable vane in which the cooling efficiency is further improved and sealing structure disposed on an inner peripheral side to suppress leakage of sealing air and prevent invasion of combustion gas into the turbine disc and enlargement of sealing air clearance is prevented. Outwardly in the radial direction, a gap between ring segment (90) and impingement cooling plate (92) disposed on the outer periphery thereof, is divided in the axial direction by a pressure partition plate (97) extending in a circumferential direction so as to provide plural cavities adjusted to different pressures, thereby forming a cooling structure in the ring segment (90). Inside in the radial direction, a static vane inside diameter side cavity (53) and downstream cavity (31) are formed by a box (57) for sealing the static vane inside diameter side cavity (53). Further, a ring-like holding ring (38) holds a sealing piece (9) for regulating the clearance (6) communicating between the upstream cavity (31) and the downstream cavity (32).
摘要翻译：一种具有冷却结构的燃气轮机，其设置在可动叶片的径向外侧的外周侧，其中冷却效率进一步提高，密封结构设置在内周侧，以抑制密封空气的泄漏并防止燃烧气体入侵防止涡轮盘和密封空气间隙的增大。在径向方向上，设置在其外周上的环形段（90）和冲击冷却板（92）之间的间隙在轴向方向上被沿圆周方向延伸的压力分隔板（97）分开，从而提供调节到不同压力的多个空腔，从而在环形段（90）中形成冷却结构。在径向内部，通过用于密封静态叶片内径侧腔（53）的盒（57）形成静止叶片内径侧空腔（53）和下游空腔（31）。此外，环状保持环（38）保持用于调节在上游空腔（31）和下游空腔（32）之间连通的间隙（6）的密封件（9）。

58. 发明授权

US6099244A Cooled stationary blade for a gas turbine 失效
标题翻译：用于燃气轮机的冷却固定叶片
公开(公告)号：US6099244A
公开(公告)日：2000-08-08
申请号：US38376
申请日：1998-03-11
申请人： Yasuoki Tomita , Hiroki Fukuno , Kiyoshi Suenaga
发明人： Yasuoki Tomita , Hiroki Fukuno , Kiyoshi Suenaga
IPC分类号： F01D9/02 , F01D5/18 , F01D9/04 , F02C7/18 , F02D9/02 , F01D5/08
CPC分类号： F01D5/18 , F02D9/02 , F05D2260/22141 , Y02T10/14
摘要： In the present invention, seal air passes through a tube extending in a stationary blade from an outside shroud to an inside shroud, flows into a cavity to keep the pressure in the cavity high so as to seal the high-temperature combustion gas, and is discharged to a passage. Part of cooling air flows into an air passage to cool the leading edge portion, passes through the peripheral portion of the inside shroud to cool the same, and is discharged to a passage. The remaining cooling air flows into a passage, passes through a serpentine cooling flow path consisting of air passages having turbulators, and is discharged through air cooling holes formed at the trailing edge. The cooling air passing through the passage at the leading edge portion cools the peripheral portion of the inside shroud as well as the leading edge portion of blade, by which the cooling efficiency is increased.
摘要翻译：在本发明中，密封空气通过从外侧护罩延伸到内侧护罩的固定刀片的管道流入空腔，以将空腔内的压力保持在较高高度以密封高温燃烧气体，并且是排到通道。一部分冷却空气流入空气通道以冷却前缘部分，通过内侧护罩的周边部分使其冷却，并且排出到通道中。剩余的冷却空气流入通道，通过由具有湍流器的空气通道组成的蛇形冷却流路，并通过形成在后缘的空气冷却孔排出。通过前缘部分的通道的冷却空气冷却内部护罩的周边部分以及叶片的前缘部分，从而冷却效率提高。

59. 发明授权

US5997245A Cooled shroud of gas turbine stationary blade 失效
标题翻译：燃气轮机固定叶片的冷却罩
公开(公告)号：US5997245A
公开(公告)日：1999-12-07
申请号：US64987
申请日：1998-04-23
申请人： Yasuoki Tomita , Hiroki Fukuno , Hideki Murata , Kiyoshi Suenaga
发明人： Yasuoki Tomita , Hiroki Fukuno , Hideki Murata , Kiyoshi Suenaga
IPC分类号： F01D9/02 , F01D5/18 , F01D9/04 , F02C7/18
CPC分类号： F01D9/041 , F01D5/187 , F05D2240/81 , F05D2260/2212
摘要： The invention relates to a cooled shroud in a gas turbine stationary blade which is able to flow a cooling air in the entire area of an inner shroud for cooling thereof. Three stationary blades are fixed to the inner shroud 2, a cover 13, 14 is provided to form a space 21 and space 22a, 22b and 22c, respectively. The cooling air is introduced through an independent air passage 3A of a leading edge of each stationary blade into the spaces 22a, 22b and 22c and is flown therefrom through a tunnel 18 and air reservoirs 19-2, 19-3 and 19-4 to be blown out of a trailing edge while cooling surfaces of the shrouds and the trailing edges. Also, a portion of the cooling air from the space 22b is flown into the space 21 through a tunnel 11, a leading edge side passage 12 and an endmost tunnel 11 and is then blown out of the trailing edge through a tunnel 18 and an air reservoir 19-1, so that the leading edge portion, the endmost portion and the endmost trailing edge portion are cooled. By use of the independent air passage, the cooling air is introduced to cool the entire area of the shroud.
摘要翻译：本发明涉及一种能够在内护罩的整个区域内流动冷却空气的燃气轮机固定叶片中的冷却罩，用于冷却。三个固定叶片固定在内护罩2上，盖13,14设置成分别形成空间21和空间22a，22b和22c。冷却空气通过每个固定叶片的前缘的独立空气通道3A引入空间22a，22b和22c中，并且通过隧道18和空气储存器19-2,19-3和19-4从其中流动到从后缘吹出，同时冷却护罩和后缘的表面。此外，来自空间22b的一部分冷却空气通过隧道11，前缘侧通道12和最终通道11流入空间21，然后通过隧道18和空气吹出后缘储存器19-1，使得前缘部分，最末端部分和最末端后缘部分被冷却。通过使用独立的空气通道，引入冷却空气以冷却护罩的整个区域。

60. 发明授权

US5915923A Gas turbine moving blade 失效
标题翻译：燃气轮机动叶片
公开(公告)号：US5915923A
公开(公告)日：1999-06-29
申请号：US861753
申请日：1997-05-22
申请人： Yasuoki Tomita , Taku Ichiryu , Kiyoshi Suenaga
发明人： Yasuoki Tomita , Taku Ichiryu , Kiyoshi Suenaga
IPC分类号： F01D5/18 , F16D5/18
CPC分类号： F01D5/187 , F05D2240/81 , F05D2260/205 , F05D2260/2322
摘要： A gas turbine moving blade in which the moving blade operating in a high temperature operating gas is cooled from its interior by steam and the steam after being used for the cooling is recovered, by use of a simple structure. A supply side passage (10), through which steam (6) is supplied directly into a cooling passage (51) of a blade leading edge side (11), is provided within a blade root portion (2) and a pocket (19). One end of the pocket is connected to the supply side passage and the other end of which is connected to a cooling passage (52) of a blade trailing edge side (12). The pocket is covered with a plate, which extends in a blade chord direction on an outer peripheral side face of the blade root portion between a blade platform and a rotor plate. Thus, efficiency of the gas turbine can be effectively enhanced.
摘要翻译：一种燃气轮机动叶片，其中在高温操作气体中操作的移动叶片由其内部由蒸汽冷却，并且在用于冷却之后蒸汽被回收，通过使用简单的结构。供给侧通道（10）设置在叶片根部（2）和袋（19）内，蒸汽（6）直接供给到叶片前缘侧（11）的冷却通道（51）。袋的一端连接到供给侧通道，另一端连接到叶片后缘侧（12）的冷却通道（52）。该口袋被覆盖有板，其在刀片平台和转子板之间的叶片根部的外周侧面上以叶片弦方向延伸。因此，能够有效地提高燃气轮机的效率。

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