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1.发明授权Tail tube seal structure of combustor and a gas turbine using the same structure 有权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
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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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。
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公开(公告)号：US06761529B2
公开(公告)日：2004-07-13
申请号：US10202654
申请日：2002-07-25
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.
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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.
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公开(公告)号：US06742991B2
公开(公告)日：2004-06-01
申请号：US10192676
申请日：2002-07-11
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。
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公开(公告)号：US06692227B2
公开(公告)日：2004-02-17
申请号：US10025533
申请日：2001-12-26
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。
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公开(公告)号：US07168914B2
公开(公告)日：2007-01-30
申请号：US11246227
申请日：2005-10-11
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。
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公开(公告)号：US20060177301A1
公开(公告)日：2006-08-10
申请号：US11246227
申请日：2005-10-11
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.
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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。
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公开(公告)号：US20050135925A1
公开(公告)日：2005-06-23
申请号：US10820744
申请日：2004-04-09
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 low 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.
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