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1. 发明授权

US06602048B2 Gas turbine split ring 有权
公开(公告)号：US06602048B2
公开(公告)日：2003-08-05
申请号：US09998201
申请日：2001-12-03
申请人： Tatsuaki Fujikawa , Yasuoki Tomita , Shunsuke Torii , Ryotaro Magoshi , Masamitsu Kuwabara , Shinichi Inoue
发明人： Tatsuaki Fujikawa , Yasuoki Tomita , Shunsuke Torii , Ryotaro Magoshi , Masamitsu Kuwabara , Shinichi Inoue
IPC分类号： F01D1124
CPC分类号： F01D11/08 , F01D9/00 , F01D11/18 , F05D2250/181 , F05D2250/282 , F05D2260/201 , F05D2260/30
摘要： In the gas turbine split ring, on an outer peripheral surface 1b between two cabin attachment flanges, a circumferential rib which extends in the circumferential direction and an axial rib which extends in the axial direction and has a height taller than that of the circumferential rib are, respectively, formed in plural lines, so that it is possible to suppress heat deformation in the axial direction which largely contributes to reduction of the tip clearance compared to head deformation in the circumferential direction more efficiently.

2. 发明授权

US06893215B2 Division wall and shroud of gas turbine 有权
标题翻译：燃气轮机壁和护罩
公开(公告)号：US06893215B2
公开(公告)日：2005-05-17
申请号：US10025593
申请日：2001-12-26
申请人： Masamitsu Kuwabara , Yoshiyuki Morii , Yasuoki Tomita , Shunsuke Torii , Shigehiro Shiozaki , Kotaro Ohshima , Tatsuaki Fujikawa , Ryotaro Magoshi , Shinichi Inoue
发明人： Masamitsu Kuwabara , Yoshiyuki Morii , Yasuoki Tomita , Shunsuke Torii , Shigehiro Shiozaki , Kotaro Ohshima , Tatsuaki Fujikawa , Ryotaro Magoshi , Shinichi Inoue
IPC分类号： F01D5/34 , F01D9/02 , F01D9/04 , F01D11/00 , F01D25/24 , F01D25/26
CPC分类号： F01D11/005 , F01D11/006 , F01D11/008
摘要： The division wall is made up of a plurality of division wall sections forming a passage wall of high temperature gas which are connected in the direction of arrangement of blades to form a wall surface having a roughly circular cross section as a whole, a gas flow restricting structure for preventing high temperature gas from passing through a gap formed at a connecting portion between the division wall sections in the flow direction of the high temperature gas from the opening on the upstream side of the high temperature gas in the gap, or a gas flow restricting structure for preventing the high temperature gas from being embraced in the gap, for example, a sealing member formed into a prism having a T-shape cross section as a whole composed of a plane portion as a sealing portion and a projected portion for filling the gap is provided.
摘要翻译：分隔壁由多个分隔壁部分构成，形成高温气体的通道壁，其沿着叶片的排列方向连接以形成整个具有大致圆形横截面的壁表面，结构，用于防止高温气体从形成在高温气体的流动方向上的分隔壁部分之间的连接部分处的间隙从间隙中的高温气体的上游侧的开口或气流限制结构用于防止高温气体包围在间隙中，例如，形成为具有作为整体的T形横截面的棱镜的密封构件由作为密封部分的平面部分和用于填充的突出部分组成提供了差距。

3. 发明授权

US06692227B2 Stationary blade shroud of a gas turbine 有权
标题翻译：燃气轮机的固定叶片护罩
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。

4. 发明授权

US06616405B2 Cooling structure for a gas turbine 有权
公开(公告)号：US06616405B2
公开(公告)日：2003-09-09
申请号：US09998668
申请日：2001-12-03
申请人： Shunsuke Torii , Jun Kubota , Yasuoki Tomita , Hiroyuki Aoki , Masamitsu Kuwabara
发明人： Shunsuke Torii , Jun Kubota , Yasuoki Tomita , Hiroyuki Aoki , Masamitsu Kuwabara
IPC分类号： F01D900
CPC分类号： F01D25/12 , F01D5/186 , F05D2240/81 , Y10S415/914
摘要： In a cooling structure for a gas turbine, cooling air diffusion holes are formed from inner surface to outer surface of a platform so as to open from high pressure side blade surface of a moving blade offset in a direction toward low pressure side blade surface of adjacent moving blade confronting the high pressure side blade surface, in a direction of primary flow.

5. 发明授权

US06761529B2 Cooling structure of stationary blade, and gas turbine 有权
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.

6. 发明授权

US07168914B2 Gas turbine stationary blade 有权
标题翻译：燃气轮机固定叶片
公开(公告)号：US07168914B2
公开(公告)日：2007-01-30
申请号：US11246227
申请日：2005-10-11
申请人： Shigehiro Shiozaki , Masamitsu Kuwabara , Yasuoki Tomita
发明人： Shigehiro Shiozaki , Masamitsu Kuwabara , Yasuoki Tomita
IPC分类号： F01D9/06
CPC分类号： F01D11/005 , B23K26/389 , F01D5/18 , F01D5/187 , F01D5/188 , F01D9/041 , F05D2240/80 , F05D2240/81 , F05D2260/201 , F05D2260/2212
摘要： The gas turbine stationary blade comprises a stationary blade section provided therein with a passage for cooling air, an inner shroud for supporting the stationary blade section on the side of a discharge port of the cooling air, and a plurality of segments each of which includes at least one stationary blade section and at least one inner shroud. A flow passage is pulled out from the discharge port of the cooling air, and the flow passage is introduced to a front edge corner section of the inner shroud and is extended rearward along a side edge of the inner shroud.
摘要翻译：燃气轮机固定叶片包括设置有用于冷却空气的通道的固定叶片部分，用于在冷却空气的排出口的侧面支撑固定叶片部分的内护罩，以及多个部分，每个部分包括在至少一个固定叶片部分和至少一个内部护罩。流动通道从冷却空气的排出口被拉出，并且流动通道被引入内护罩的前边缘角部并且沿内护罩的侧边缘向后延伸。

7. 发明申请

US20060177301A1 Gas turbine stationary blade 有权
公开(公告)号：US20060177301A1
公开(公告)日：2006-08-10
申请号：US11246227
申请日：2005-10-11
申请人： Shigehiro Shiozaki , Masamitsu Kuwabara , Yasuoki Tomita
发明人： Shigehiro Shiozaki , Masamitsu Kuwabara , Yasuoki Tomita
IPC分类号： F03B11/00
CPC分类号： F01D11/005 , B23K26/389 , F01D5/18 , F01D5/187 , F01D5/188 , F01D9/041 , F05D2240/80 , F05D2240/81 , F05D2260/201 , F05D2260/2212
摘要： The gas turbine stationary blade comprises a stationary blade section provided therein with a passage for cooling air, an inner shroud for supporting the stationary blade section on the side of a discharge port of the cooling air, and a plurality of segments each of which includes at least one stationary blade section and at least one inner shroud. A flow passage is pulled out from the discharge port of the cooling air, and the flow passage is introduced to a front edge corner section of the inner shroud and is extended rearward along a side edge of the inner shroud.

8. 发明授权

US06318960B1 Gas turbine stationary blade 有权
标题翻译：燃气轮机固定叶片
公开(公告)号：US06318960B1
公开(公告)日：2001-11-20
申请号：US09522008
申请日：2000-03-09
申请人： Masamitsu Kuwabara , Yasuoki Tomita , Eisaku Ito
发明人： Masamitsu Kuwabara , Yasuoki Tomita , Eisaku Ito
IPC分类号： F01D514
CPC分类号： F01D5/145 , F01D5/186 , F01D5/189 , F05D2260/201 , F05D2260/202 , F05D2260/607
摘要： A gas turbine stationary blade having passages (23, 24) that are provided in the stationary blade (10). A front cylindrical insert (2) is provided in the passage (23) and a rear cylindrical insert (5) is provided in the passage (24), and the inserts are supported at two supporting portions (3a, 3b), (6a, 6b), respectively. A projection (1) is provided at a leading edge portion of the blade so that the leading edge, where the thermal loads are high, is made smaller in size and the number of rows of cooling holes (11a) in the leading edge portion is reduced. Air blowing holes (4b) are provided on the dorsal side rear portion of the front insert (2) and film cooling holes (12) are provided on the dorsal side of the blade, both have diameters that are larger than other air blowing and cooling holes provided in the insert (2) and the blade (10), so that dust in the cooling air is caused to flow out, thereby preventing clogging of the holes. The curved surface of the blade leading edge portion is formed on an elliptical curve, so that the cooling air is caused to flow smoothly. Also, curved surfaces of fillets are formed on an elliptical curve so that thermal stresses concentrated near the fillets are avoided.
摘要翻译：一种具有设置在固定叶片（10）中的通道（23,24）的燃气轮机固定叶片。在所述通道（23）中设置有前圆柱形插入件（2），并且在所述通道（24）中设置有后圆柱形插入件（5），并且所述插入件支撑在两个支撑部分（3a，3b）处，（6a， 6b）。突起（1）设置在叶片的前缘部，使得热负荷高的前缘的尺寸变小，并且前缘部的冷却孔（11a）的排数为减少在前插入件（2）的背侧后部设置有空气吹入孔（4b），并且在叶片的背侧设置有膜冷却孔（12），其直径大于其他空气吹送和冷却设置在插入件（2）和叶片（10）中的孔，使得冷却空气中的灰尘流出，从而防止孔堵塞。叶片前缘部的曲面形成在椭圆曲线上，使得冷却空气顺利地流动。此外，圆角的曲面形成在椭圆曲线上，从而避免了集中在圆角附近的热应力。

9. 发明授权

US06988872B2 Turbine moving blade and gas turbine 有权
标题翻译：涡轮动叶片和燃气轮机
公开(公告)号：US06988872B2
公开(公告)日：2006-01-24
申请号：US10351479
申请日：2003-01-27
申请人： Friedrich Soechting , Charles Ellis , Yasuoki Tomita , Shunsuke Torii
发明人： Friedrich Soechting , Charles Ellis , Yasuoki Tomita , Shunsuke Torii
IPC分类号： B63H1/14
CPC分类号： F01D5/186 , F01D5/187 , F05D2260/22141 , Y02T50/676
摘要： The object of the present invention is to provide a turbine moving blade that has high heat resistance and can be used for a long period of time by improving the cooling efficiency of the turbine moving blade, and to improve both the thermal efficiency and operating efficiency of a gas turbine through the use of this turbine moving blade. In order to achieve the object, the present invention provide a turbine moving blade arranged in a combustion gas flow path in which a plurality of blow-out openings for blowing out a cooling medium are formed in its outer surface, wherein among a plurality of cooling medium trailing edge blow-out openings arranged from the vicinity of a blade base to the vicinity of a blade tip along a blade trailing edge of turbine moving blade, the opening area of a blade tip trailing edge blow-out opening located in the vicinity of blade tip is set to be larger than the opening area of the other trailing edge blow-out openings.
摘要翻译：本发明的目的是提供一种具有高耐热性并可通过提高涡轮机动叶片的冷却效率而长时间使用的涡轮机动叶片，并提高热效率和操作效率通过使用该涡轮机动叶片的燃气轮机。为了实现该目的，本发明提供了一种设置在燃烧气体流路中的涡轮机动叶片，其中在其外表面形成有用于吹出冷却介质的多个吹出口，其中在多个冷却从叶片底部附近到涡轮机动叶片的叶片后缘的叶片尖端附近布置的中间后缘吹出开口，位于涡轮机动叶片附近的叶片尖端后缘吹出开口的开口面积叶片尖端被设定为大于其他后缘吹出口的开口面积。

10. 发明授权

US06751962B1 Tail tube seal structure of combustor and a gas turbine using the same structure 有权
标题翻译：采用相同结构的燃烧器和燃气轮机的尾管密封结构
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。

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