公开(公告)号：US06751962B1

公开(公告)日：2004-06-22

申请号：US09521413

申请日：2000-03-08

申请人： Masamitsu Kuwabara ,  Yasuoki Tomita ,  Kiyoshi Suenaga ,  Masahito Kataoka ,  Yoshichika Sato ,  Koji Watanabe

发明人： Masamitsu Kuwabara ,  Yasuoki Tomita ,  Kiyoshi Suenaga ,  Masahito Kataoka ,  Yoshichika Sato ,  Koji Watanabe

IPC分类号： F23R360

CPC分类号： F01D9/023 ,  F23R3/60

摘要： In a tail tube seal structure of gas turbine, a U-shaped groove is provided at one side of a tail tube seal where a flange of a tail tube outlet is fitted, and a pi-shaped groove is provided at other side of the tail tube seal where a gas pass side flange end is fitted, thereby composing the seal of the connection area. Inclined cooling holes are drilled in the tail tube seal in addition to the cooling holes existing conventionally. The cooling air flows in from the inclined holes and cools the gas pass side of the groove due to the film effect. Therefore, the difference in thermal expansion between the groove and flange end is decreased, the wear of this area is decreased, and the reliability of the seal is enhanced.

摘要翻译： 在燃气轮机的尾管密封结构中，在尾管密封件的一侧设置有U形槽，其中尾管出口的凸缘被装配，并且在该尾部的另一侧设置有一个pi形槽 管密封件，其中安装有气体通过侧凸缘端，从而构成连接区域的密封。 除了常规存在的冷却孔之外，还在尾管密封件中钻出倾斜的冷却孔。 冷却空气从倾斜孔流入，由于膜效应而冷却槽的气体通过侧。 因此，凹槽和凸缘端之间的热膨胀差异减小，该区域的磨损减小，并且密封件的可靠性提高。

公开(公告)号：US06742991B2

公开(公告)日：2004-06-01

申请号：US10192676

申请日：2002-07-11

申请人： Friedrich Soechting ,  Satoshi Hada ,  Masamitsu Kuwabara ,  Junichiro Masada ,  Yasuoki Tomita

发明人： Friedrich Soechting ,  Satoshi Hada ,  Masamitsu Kuwabara ,  Junichiro Masada ,  Yasuoki Tomita

IPC分类号： F01D518

CPC分类号： F01D5/188 ,  F01D5/186 ,  F01D5/189 ,  F05D2250/70 ,  F05D2260/202

摘要： A turbine blade applicable to a gas turbine has a turbine blade body having film cooling holes, the interior space of which is partitioned into two cavities by a rib. Hollow inserts each having impingement holes are respectively arranged in the cavities to form cooling spaces therebetween. Communication is ensured between the cavities by bypass hole and slits, so that the impingement cooling is interrupted with respect to the prescribed side having a good heat transmission in the turbine blade body. A partition wall is further arranged between the rib and the insert arranged in the trailing-edge side, thus providing a separation between the cooling spaces respectively arranged in the rear side and front side. Thus, it is possible to noticeably reduce the amount of cooling air in the turbine blade body; and it is possible to reduce temperature differences entirely over the turbine blade body as small as possible.

摘要翻译： 适用于燃气轮机的涡轮叶片具有涡轮叶片体，其具有膜冷却孔，其内部空间通过肋分隔成两个空腔。 各个具有冲击孔的中空插入件分别设置在空腔中，以在它们之间形成冷却空间。 通过旁通孔和狭缝确保空腔之间的通信，使得冲击冷却相对于在涡轮叶片体中具有良好的热传递的规定侧被中断。 分隔壁还布置在布置在后缘侧的肋和插入件之间，从而在分别布置在后侧和前侧的冷却空间之间分开。 因此，可以显着地减少涡轮叶片体内的冷却空气量; 并且可以尽可能小地将涡轮叶片体上的温差完全降低。

公开(公告)号：US06692227B2

公开(公告)日：2004-02-17

申请号：US10025533

申请日：2001-12-26

申请人： Yasuoki Tomita ,  Masamitsu Kuwabara ,  Shunsuke Torii

发明人： Yasuoki Tomita ,  Masamitsu Kuwabara ,  Shunsuke Torii

IPC分类号： F01D1112

CPC分类号： F01D5/225 ,  F01D11/001 ,  F01D11/005

摘要： A base plate and honeycomb member disposed at the inner circumference side of an inside shroud are fixed to the inside shroud, at a phase deviation in the peripheral direction, with respect to the inside shroud, so as to plug the missing range of seal member, out of gaps between adjacent inside shrouds, and therefore leakage of purge air from the missing range of seal member is prevented without adding new constituent members.

摘要翻译： 设置在内侧护罩的内周侧的基板和蜂窝构件相对于内侧护罩以周向的相位偏移固定在内侧护罩上，从而堵塞密封构件的缺失范围， 在相邻的内部护罩之间的间隙之外，并且因此防止吹扫空气从密封构件的缺失范围泄漏，而不添加新的构成构件。

公开(公告)号：US06508623B1

公开(公告)日：2003-01-21

申请号：US09959310

申请日：2001-10-22

申请人： Shigehiro Shiozaki ,  Yasuoki Tomita

发明人： Shigehiro Shiozaki ,  Yasuoki Tomita

IPC分类号： F01D1124

CPC分类号： F01D25/12 ,  F01D9/04 ,  F01D11/08 ,  F01D25/246 ,  F05D2260/201

摘要： A gas turbine segmental ring has an increased rigidity to suppress a thermal deformation and enables less cooling air leakage by less number of connecting portions of segment structures. Cooling air (70) from a compressor flows through cooling holes (61) of an impingement plate (60) to enter a cavity (62) and to impinge on a segmental ring (1) for cooling thereof. The cooling air (70) further flows into cooling passages (64) from openings (63) of the cavity (62) for cooling an interior of the segmental ring (1) and is discharged into a gas path from openings of a rear end of the segmental ring (1). Waffle pattern (10) of ribs arranged in a lattice shape is formed on an upper surface of the segmental ring (1) to thereby increase the rigidity. A plurality of slits (6) are formed in flanges (4, 5) extending in the turbine circumferential direction to thereby absorb the deformation and thermal deformation of the segmental ring (1) is suppressed.

摘要翻译： 燃气轮机节段环具有增加的刚性以抑制热变形，并且通过较少数量的节段结构的连接部分能够减少冷却空气泄漏。 来自压缩机的冷却空气（70）流过冲击板（60）的冷却孔（61）进入空腔（62）并撞击节段环（1）以进行冷却。 冷却空气（70）进一步从空腔（62）的开口（63）流入冷却通道（64），用于冷却节段环（1）的内部，并从其后端的开口排出气体通道 节段环（1）。 排列成格子状的肋的楔形花纹（10）形成在节段环（1）的上表面上，从而增加刚性。 多个狭缝（6）形成在沿涡轮机圆周方向延伸的凸缘（4,5）中，从而吸收变形，并且抑制了节段环（1）的热变形。

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。

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。

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。

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。

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。

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。