公开(公告)号：US06290462B1

公开(公告)日：2001-09-18

申请号：US09272559

申请日：1999-03-19

申请人： Tatsuo Ishiguro ,  Koji Watanabe ,  Masaaki Matsuura ,  Kenichiro Takeishi ,  Junichiro Masada ,  Yasuoki Tomita ,  Kiyoshi Suenaga

发明人： Tatsuo Ishiguro ,  Koji Watanabe ,  Masaaki Matsuura ,  Kenichiro Takeishi ,  Junichiro Masada ,  Yasuoki Tomita ,  Kiyoshi Suenaga

IPC分类号： F01D1100

CPC分类号： F01D5/187 ,  F05D2250/185 ,  F05D2260/2212

摘要： A gas turbine cooled blade is constructed without an increase in the number of parts or time requirements, in which seal air is maintained at a lower temperature with the heat exchange rate being suppressed, and the heat transfer rate of the cooling medium in cooling passage is enhanced. A plurality of cooling passages (A, B, C, D, E) is provided in a blade, and the first row cooling passage (A) is covered at the blade inner and outer peripheries and communicates with the second row cooling passage (B) through communication holes (6) and with the main flow gas path through film cooling holes (7). The second row cooling passage (B) communicates with the blade inner peripheral cavity (10) to form a seal air supply passage. A plurality of ribs (31) are disposed on the inner wall of cooling passage (22) with a predetermined pitch (P). The ribs are arranged alternately and are inclined against cooling medium flow with respective higher first end contacting lower side faces of an immediately upstream rib at a position on both side portions of cooling passage (22). High heat transfer rate areas are formed on both side portions of cooling passage (22), and the average heat transfer rate in cooling passage is enhanced.

摘要翻译： 在不增加部件或时间要求的情况下构建燃气轮机冷却叶片，其中密封空气在热交换率被抑制下保持在较低温度，并且冷却通道中的冷却介质的传热速率为 增强。 多个冷却通道（A，B，C，D，E）设置在叶片中，第一排冷却通道（A）被覆盖在叶片的内周和外周，并与第二排冷却通道 ）通过连通孔（6）并且主流动气体通道通过膜冷却孔（7）。 第二排冷却通道（B）与叶片内周腔（10）连通，形成密封空气供给通道。 多个肋（31）以预定的间距（P）设置在冷却通道（22）的内壁上。 这些肋交替布置并且相对于冷却介质流倾斜，并且在冷却通道（22）的两侧部分的位置处，相应较高的第一端接触紧紧上游的肋的下侧面。 在冷却通道（22）的两侧形成有高的传热率区域，并且冷却通路的平均传热率提高。

公开(公告)号：US6092983A

公开(公告)日：2000-07-25

申请号：US202594

申请日：1998-12-17

申请人： Yasuoki Tomita ,  Sunao Aoki ,  Kiyoshi Suenaga ,  Tatsuo Ishiguro

发明人： Yasuoki Tomita ,  Sunao Aoki ,  Kiyoshi Suenaga ,  Tatsuo Ishiguro

IPC分类号： F01D5/18 ,  F01D9/02 ,  F01D9/06 ,  F01D9/04

CPC分类号： F01D9/065 ,  F01D5/187 ,  F01D9/02 ,  F05D2240/10 ,  F05D2240/81 ,  F05D2260/22141

摘要： In a cooled stationary blade assembly for a gas turbine, an interior of a blade and an inner shroud are cooled by steam to eliminate the use of air cooling. Steam passages 33A, 33B, 33C, 33D, 33E and 33F are provided in the stationary blade 30. The cooling steam 39 is introduced from the steam passage 33A on the front edge side through an outer shroud and passes, in order, through the steam passages 33B, 33C, 33D, and 33E to flow into the steam passage 33F at the rear edge side to cool the interior of the blade, and is recovered through the outer shroud from the upper portion of the steam passage 33F. A portion of the steam from the steam passage 33A is introduced into the inner shroud 31, enters to steam passages 20 from a steam introduction passage 22, branches to the right and left through both end portions, and flows out into the steam passage 33F at the rear edge from a steam discharge passage 21. Not only the interior of the blade, but also the interior of the inner shroud 31 is cooled by the steam so that the cooling air is dispensed with.

摘要翻译： PCT No.PCT / JP98 / 01958 371日期1998年12月17日第 102（e）1998年12月17日日期PCT提交1998年4月28日PCT公布。 出版物WO98 / 50684 日期1998年11月12日在用于燃气轮机的冷却固定叶片组件中，叶片和内罩的内部由蒸汽冷却以消除空气冷却的使用。 蒸汽通道33A，33B，33C，33D，33E和33F设置在固定叶片30中。冷却蒸汽39通过外护罩从前边缘侧的蒸汽通道33A引入，并依次通过蒸汽 通道33B，33C，33D和33E在后边缘侧流入蒸汽通道33F以冷却叶片的内部，并通过外护罩从蒸汽通道33F的上部回收。 来自蒸汽通道33A的蒸汽的一部分被引入内罩31，从蒸汽引入通道22进入蒸汽通道20，通过两个端部向右和向左分支，并且流出到蒸汽通道33F中 来自蒸汽排出通道21的后边缘。不仅叶片的内部，而且内部护罩31的内部都被蒸汽冷却，从而省去了冷却空气。

公开(公告)号：US06481967B2

公开(公告)日：2002-11-19

申请号：US09790975

申请日：2001-02-23

申请人： Yasuoki Tomita ,  Yukihiro Hashimoto ,  Kiyoshi Suenaga ,  Hisato Arimura ,  Shunsuke Torii ,  Jun Kubota ,  Akihiko Shirota ,  Sunao Aoki ,  Tatsuo Ishiguro

发明人： Yasuoki Tomita ,  Yukihiro Hashimoto ,  Kiyoshi Suenaga ,  Hisato Arimura ,  Shunsuke Torii ,  Jun Kubota ,  Akihiko Shirota ,  Sunao Aoki ,  Tatsuo Ishiguro

IPC分类号： F01D518

CPC分类号： F01D5/20 ,  F01D5/186 ,  F01D5/187 ,  F05D2240/81 ,  F05D2250/185 ,  F05D2260/22141

摘要： A gas turbine moving blade is provided which prevents occurrence of cracks caused by thermal stresses due to temperature differences between a blade and a platform while the gas turbine is being stopped. During steady operation time of the moving blade, cooling air enters cooling passages to flow through other cooling passages for cooling the blade, and then to flow out of the blade. A recessed portion having a smooth curved surface is provided in the platform near a blade fitting portion on the blade trailing edge side. A fillet of the blade fitting portion on the blade trailing edge side has a curved surface with curvature larger than that of a conventional blade fitting portion. A hub slot below the fillet, for blowing air, has a cross sectional area larger than other slots of the blade trailing edge. A thermal barrier coating is applied to the blade surface. By the above construction, thermal stresses due to temperature differences between the blade and the platform during gas turbine stoppage are made smaller and occurrence of cracks is prevented.

摘要翻译： 提供了一种燃气轮机动叶片，其防止在燃气轮机停止时由于叶片和平台之间的温度差引起的热应力的发生。 在运动叶片的稳定运行时间内，冷却空气进入冷却通道，流过其它冷却通道，以冷却叶片，然后流出叶片。 具有光滑曲面的凹部在叶片后缘侧的叶片嵌合部附近设置在平台上。 叶片后缘侧的叶片嵌合部的圆角具有比现有的叶片嵌合部曲率大的曲率的曲面。 在圆角下方的用于吹送空气的轮毂槽的横截面积大于叶片后缘的其它槽。 将热障涂层施加到叶片表面。 通过上述结构，使得在燃气轮机停止期间由于叶片和平台之间的温度差导致的热应力变小，并且防止了裂纹的发生。

公开(公告)号：US06257830B1

公开(公告)日：2001-07-10

申请号：US09230983

申请日：1999-06-02

申请人： Masaaki Matsuura ,  Kiyoshi Suenaga ,  Sunao Aoki ,  Kazuo Uematsu ,  Hiroki Fukuno ,  Yasuoki Tomita

发明人： Masaaki Matsuura ,  Kiyoshi Suenaga ,  Sunao Aoki ,  Kazuo Uematsu ,  Hiroki Fukuno ,  Yasuoki Tomita

IPC分类号： F01D518

CPC分类号： F01D5/147 ,  F01D5/187 ,  F05D2260/2322

摘要： In a steam cooling system proposed heretofore, high-pressure steam is supplied into an internal space of a blade for effecting cooling thereof with the high-pressure steam to thereby recover heat energy. This system however suffers from problems concerning the strength of the blade and the like. The present invention solves these problems and provides a gas-turbine blade which does not suffer from problems concerning the strength thereof nor problems concerning the flow of high-pressure steam. To this end, a coolant flow passage is formed within the blade extending in the longitudinal direction of the blade, and reinforcing ribs which interconnects a dorsal wall and a ventral wall of the blade is disposed within the coolant flow passage so as to extend in the flow direction of the coolant. Hence, the strength of the blade can be ensured without any obstacle to the flow of the coolant.

摘要翻译： 在迄今为止提出的蒸汽冷却系统中，将高压蒸汽供应到叶片的内部空间中，以利用高压蒸汽冷却，从而回收热能。 然而，该系统存在关于叶片等的强度的问题。 本发明解决了这些问题，提供了一种不存在与强度相关的问题的燃气轮机叶片，也不会涉及高压蒸汽的流动问题。 为此，在刀片的纵向延伸的叶片内形成冷却剂流动通道，并且将与叶片的背壁和腹壁相互连接的加强筋设置在冷却剂流动通道内，以便在 冷却液的流动方向。 因此，可以确保叶片的强度，而不会妨碍冷却剂的流动。

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：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：US06270311B1

公开(公告)日：2001-08-07

申请号：US09518644

申请日：2000-03-03

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： F01D100

CPC分类号： F01D11/005 ,  F05D2260/202

摘要： In gas turbine split rings, end faces having bent surfaces are formed in flanges. Adjoining split rings are coupled together with a groove therebetween to form a cylindrical split ring. Notches are formed in the flanges. These notches are sealed by inserting a seal plate into the notches of adjoining split rings. A hole for passing cooling air is drilled obliquely in the flange. Cooling air is allowed to flow out along the direction of rotation (of the turbine). This cooling air cools the outlet of the groove due to the effect of film cooling. Because of such cooling, high temperature gas is prevented from staying in this area, cooling effect is enhanced, and hence burning of the end portions can be prevented.

摘要翻译： 在燃气涡轮分裂环中，具有弯曲表面的端面形成为凸缘。 相邻的开口环与它们之间的槽耦合在一起以形成圆柱形的开口环。 在法兰上形成凹口。 这些凹口通过将密封板插入相邻的分隔环的凹口中而被密封。 用于通过冷却空气的孔倾斜地在法兰上钻出。 允许冷却空气沿着涡轮机的旋转方向流出。 由于薄膜冷却的作用，该冷却空气冷却槽的出口。 由于这样的冷却，防止高温气体停留在该区域，因此冷却效果增强，因此可以防止端部的燃烧。

公开(公告)号：US06761529B2

公开(公告)日：2004-07-13

申请号：US10202654

申请日：2002-07-25

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： F01D906

CPC分类号： F01D5/187 ,  F01D9/041 ,  F05D2240/81 ,  F05D2260/201

摘要： A collision plate having plural small holes is provided at an interval from a bottom surface of an inner shroud to form a chamber and guides cooling air from the small holes into the chamber. A leading edge flow path is provided at a leading edge side along a width direction and introduces the cooling air. A side flow path is provided along both sides of the inner shroud and guides the cooling air to a trailing edge side. A header is formed along the width direction near the trailing edge and guides the cooling air from the side flow path. Plural trailing edge flow paths are formed at the trailing edge side at intervals along a width direction, in which one end of each flow path is connected to the header and the other end is open at the trailing edge, and the cooling air in the header is ejected from the trailing edge.

公开(公告)号：US06887039B2

公开(公告)日：2005-05-03

申请号：US10191448

申请日：2002-07-10

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： F01D9/02 ,  F01D11/02 ,  F02C7/28 ,  F01D11/00

CPC分类号： F01D11/02 ,  F02C7/28

摘要： A stationary blade of a gas turbine, which can reduce thermal stress produced at a portion in the vicinity of a rear edge of an inner shroud of the stationary blade. The stationary blade is positioned adjacent to at least one of moving-blade disks in an axial direction of the gas turbine. A concave portion is provided in the inner shroud in a manner such that the concave portion is formed in the vicinity of a rear edge of the inner shroud and on an inner-peripheral face of the inner shroud, where cooling air passes along the inner-peripheral face which faces a rotation shaft of the moving-blade disks; and a protruding portion which protrudes towards the rotation shaft is formed at the rear edge of the inner shroud.

摘要翻译： 燃气轮机的固定叶片，其可以降低在固定叶片的内护罩的后边缘附近的部分产生的热应力。 固定叶片沿着燃气轮机的轴向方向定位成与活动叶片盘中的至少一个相邻。 在内护罩中设置有凹部，使得凹部形成在内护罩的后缘附近和内护罩的内周面附近，在内罩的内周面上， 面向移动刀片盘的旋转轴的周边面; 并且在内护罩的后边缘处形成有朝向旋转轴突出的突出部。

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。