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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：US06572335B2
公开(公告)日：2003-06-03
申请号：US09800668
申请日：2001-03-08
IPC分类号： F04D2958
CPC分类号： F01D5/187 , F01D9/041 , F05D2240/81 , F05D2260/22141
摘要： A gas turbine cooled stationary blade has a blade structure and outer and inner shrouds enhancing cooling efficiency and preventing the occurrence of cracks due to thermal stresses. A blade (1) wall thickness, between 75% and 100% of the blade height of a blade leading edge portion, is made thicker, and the blade (1) wall thickness of other portions is made thinner, as compared with a conventional case. Protruding ribs (4) are provided on a blade (1) convex side inner wall between 0% and 100% of the blade height. A blade (1) trailing edge opening portion is made thinner than the conventional case. Outer shroud (2) is provided with cooling passages (5a, 5b) for air flow in both side end portions. Inner shroud (3) is provided with cooling passages (9a, 9b) for air flow and cooling holes (13a, 13b) for air blow in the side end portions. With the blade (1) structure and the shroud (2, 3) cooling passages (5a, 5b, 9a, 9b) and cooling holes (13a, 13b), the cooling effect is enhanced and cracks are prevented from occurring.
摘要翻译： 燃气轮机冷却的固定叶片具有叶片结构，外部和内部护罩提高冷却效率并防止由于热应力引起的裂纹。 叶片（1）的壁厚在叶片前缘部分的叶片高度的75％和100％之间变得更厚，并且其它部分的叶片（1）的壁厚比常规的情况更薄 。 突出肋（4）设置在叶片高度的0％和100％之间的叶片（1）凸侧内壁上。 叶片（1）后缘开口部分比现有技术更薄。 外护罩（2）设置有用于在两个侧端部中的空气流动的冷却通道（5a，5b）。 内护罩（3）设有用于气流的冷却通道（9a，9b）和用于在侧端部吹气的冷却孔（13a，13b）。 利用叶片（1）结构和护罩（2,3）冷却通道（5a，5b，9a，9b）和冷却孔（13a，13b），冷却效果提高，并且防止发生裂纹。
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公开(公告)号：US6146098A
公开(公告)日：2000-11-14
申请号：US242678
申请日：1999-02-22
申请人： Hiroki Fukuno , Yasuoki Tomita , Eisaku Ito
发明人： Hiroki Fukuno , Yasuoki Tomita , Eisaku Ito
CPC分类号： F01D11/10 , F01D5/18 , F01D5/187 , F01D5/225 , F05B2240/33 , F05D2240/81
摘要： A tip shroud for a moving blade that is made thin and light for use at a gas turbine downstream stage. Cooling air holes (13 to 16) having a slot shape, are formed in a tip shroud (11) of the moving blade (10). The cooling holes are opened in two side faces of the tip shroud to release the cooling air from the inside of the moving blade (10). In the upper face of the tip shroud 11, there are formed cooling air holes 20, which communicate with the higher pressure side in a combustion gas flow direction R to release the cooling air so that the cooling air flows from the higher pressure side to the lower pressure side so as to cool a high stress portion Y. A high stress portion X is likewise cooled with the cooling air coming from an adjoining moving blade. The slot shapes of the cooling air holes (13 to 16) allow the cooling air to flow widely, thereby cooling the face of the tip shroud (11), and the cooling air holes 20 cool the high stress portions X and Y effectively.
摘要翻译： PCT No.PCT / JP98 / 02689 Sec。 一九九九年二月二十二日 102（e）1999年2月22日PCT PCT 1998年6月18日PCT公布。 公开号WO98 / 59157 日期1998年12月30日用于在燃气轮机下游阶段使用的薄而轻的移动叶片的尖端罩。 具有狭槽形状的冷却气孔（13至16）形成在活动叶片（10）的尖端罩（11）中。 冷却孔在尖端护罩的两个侧面上打开，以从动叶片（10）的内部释放冷却空气。 在顶部护罩11的上表面形成有冷却空气孔20，其在燃烧气体流动方向R上与高压侧连通以释放冷却空气，使得冷却空气从高压侧流向 低压侧，以冷却高应力部分Y.同样，高应力部分X同样地冷却来自邻接的活动叶片的冷却空气。 冷却空气孔（13〜16）的槽形状允许冷却空气大量流动，从而冷却尖端罩（11）的表面，并且冷却空气孔20有效地冷却高应力部分X和Y.
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公开(公告)号：US5967745A
公开(公告)日：1999-10-19
申请号：US28662
申请日：1998-02-24
申请人： Yasuoki Tomita , Hiroki Fukuno , Eisaku Ito , Kiyoshi Suenaga
发明人： Yasuoki Tomita , Hiroki Fukuno , Eisaku Ito , Kiyoshi Suenaga
CPC分类号： F01D11/001 , F01D11/127 , F02C7/28
摘要： A gas turbine shroud and platform seal system, which is constructed so that the flow of sealing air does not disturb a combustion gas flow, and thus any aerodynamic loss is reduced. The leaking air (60) leaks from between a platform (2) of moving blade (1) and an inside shroud (12) in a stationary blade (11). At a front or upstream side of the moving blade (1), the leaking air (60) flows along a S-shaped path within a space (8, 17) formed by a projecting end portion (12b) of the shroud, a honeycomb seal (14) and a projecting portion (4) of the platform. The air eventually flows out in the same flow direction as that of the combustion gas (50) along a surface of the platform (2). At a rear side of the moving blade (1), the leaking air (60) flows along an S-shaped path within a space (6, 9) formed by a projecting end portion (2b) of the platform, a projecting end portion (12b) of the shroud, a honeycomb seal (13) and a seal plate (3). The air eventually flows out in the same direction as that of the combustion gas (50) along a surface of the shroud (12). The air (60) flows in the same direction as the combustion gas (50), and thus a flow loss is reduced. Also, the air is not easily leaked, and a cooling effect of the platform and the shroud is increased due to a film cooling effect.
摘要翻译： 一种燃气轮机罩和平台密封系统，其结构使得密封空气的流动不会干扰燃烧气体流动，因此减少了任何空气动力学损失。 泄漏的空气（60）从静止叶片（11）的活动叶片（1）的平台（2）和内侧护罩（12）之间泄漏。 在活动叶片（1）的前侧或上游侧，泄漏空气（60）沿着由护罩的突出端部（12b）形成的空间（8,17）内的S形路径流动，蜂窝 密封件（14）和平台的突出部分（4）。 空气最终沿着平台（2）的表面沿与燃烧气体（50）相同的流动方向流出。 在活动叶片（1）的后侧，泄漏空气（60）沿着由平台的突出端部（2b）形成的空间（6,9）内的S形路径流动，突出端部 （12b），蜂窝密封件（13）和密封板（3）。 空气最终沿与护罩（12）的表面沿燃烧气体（50）相同的方向流出。 空气（60）沿与燃烧气体（50）相同的方向流动，因此流动损失减少。 此外，空气不容易泄漏，并且由于膜冷却效果，平台和护罩的冷却效果增加。
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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。
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公开(公告)号：US6086329A
公开(公告)日：2000-07-11
申请号：US38070
申请日：1998-03-11
申请人： Yasuoki Tomita , Hiroki Fukuno , Eisaku Ito
发明人： Yasuoki Tomita , Hiroki Fukuno , Eisaku Ito
CPC分类号： F01D11/006
摘要： A seal plate at the platform portion of a gas turbine moving blade. The seal plate is inserted in a gap between the adjacent platforms at each end portion of a seal pin to prevent air from leaking to the outside. A groove is provided at each of four corners of the end portion of platform of the moving blade, and the seal plate is inserted to cover the gap so as to extend the end portions of the adjacent platforms, by which the gap between the platforms is blocked. A seal pin and end seal pins are inserted between the platforms to seal this portion. However, there is a gap at the end portions, so that cooling air leaks from the lower part of platform. Since the seal plate is inserted in the groove to block the gap, the sealing property is increased.
摘要翻译： 在燃气轮机动叶片的平台部分处的密封板。 密封板在密封销的每个端部处插入相邻平台之间的间隙中，以防止空气泄漏到外部。 在活动叶片的平台的端部的四个角部的每一个处设置有凹槽，并且插入密封板以覆盖间隙，以延伸相邻平台的端部，由此平台之间的间隙为 被阻止 密封销和端部密封销插入平台之间以密封该部分。 然而，在端部处存在间隙，使得冷却空气从平台的下部泄漏。 由于密封板插入凹槽以阻挡间隙，所以密封性能增加。
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公开(公告)号：US08231348B2
公开(公告)日：2012-07-31
申请号：US12304833
申请日：2007-11-27
申请人： Shunsuke Torii , Masamitsu Kuwabara , Eisaku Ito
发明人： Shunsuke Torii , Masamitsu Kuwabara , Eisaku Ito
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F01D5/18 , F01D25/12 , F05D2240/81
摘要： A platform cooling structure for a gas turbine moving blade is provided which is capable of improving cooling performance of a platform and of improving reliability of a moving blade in such a manner that a portion in the vicinity of a side edge of the platform which is away from moving blade cooling passageways and is easily influenced by thermal stress caused by high-temperature combustion gas, that is, an upper surface of the side edge is effectively cooled by guiding high-pressure cooling air, flowing to the moving blade cooling passageways, to a discharge opening formed in a surface of the platform in the vicinity of the side edge of the platform without particularly attaching an additional member such as a cover plate to the platform. A moving blade cooling passageway 17c is formed in the inside of the gas turbine moving blade. Cooling communication holes 24a and 24b, of which one ends communicate with the moving blade cooling passageway 17c and the other ends communicate with a plurality of discharge openings 22 provided in the surface of the platform in the vicinity of the side edge of the platform 5, are formed through the inside of the platform.
摘要翻译： 提供了一种用于燃气轮机动叶片的平台冷却结构，其能够改善平台的冷却性能并提高移动叶片的可靠性，使得平台的侧边缘附近的部分离开 来自动叶片冷却通道，并且容易受到由高温燃烧气体引起的热应力的影响，即通过将流过动叶片冷却通道的高压冷却空气引导到侧边缘的上表面而被有效地冷却， 排出口，其形成在平台的表面中，在平台的侧边缘附近，而不特别地将诸如盖板的附加构件附接到平台。 动叶片冷却通道17c形成在燃气轮机动叶片的内部。 一端与动叶片冷却通路17c连通的冷却连通孔24a，24b与平台5的侧缘附近设置在平台的表面的多个排出口22连通， 通过平台的内部形成。
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公开(公告)号：US20090202339A1
公开(公告)日：2009-08-13
申请号：US12304833
申请日：2007-11-27
申请人： Shunsuke Torii , Masamitsu Kuwabara , Eisaku Ito
发明人： Shunsuke Torii , Masamitsu Kuwabara , Eisaku Ito
CPC分类号： F01D5/187 , F01D5/18 , F01D25/12 , F05D2240/81
摘要： A platform cooling structure for a gas turbine moving blade is provided which is capable of improving cooling performance of a platform and of improving reliability of a moving blade in such a manner that a portion in the vicinity of a side edge of the platform which is away from moving blade cooling passageways and is easily influenced by thermal stress caused by high-temperature combustion gas, that is, an upper surface of the side edge is effectively cooled by guiding high-pressure cooling air, flowing to the moving blade cooling passageways, to a discharge opening formed in a surface of the platform in the vicinity of the side edge of the platform without particularly attaching an additional member such as a cover plate to the platform. A moving blade cooling passageway 17c is formed in the inside of the gas turbine moving blade. Cooling communication holes 24a and 24b, of which one ends communicate with the moving blade cooling passageway 17c and the other ends communicate with a plurality of discharge openings 22 provided in the surface of the platform in the vicinity of the side edge of the platform 5, are formed through the inside of the platform.
摘要翻译： 提供了一种用于燃气轮机动叶片的平台冷却结构，其能够改善平台的冷却性能并提高移动叶片的可靠性，使得平台的侧边缘附近的部分离开 来自动叶片冷却通道，并且容易受到由高温燃烧气体引起的热应力的影响，即通过将流过动叶片冷却通道的高压冷却空气引导到侧边缘的上表面而被有效地冷却， 排出口，其形成在平台的表面中，在平台的侧边缘附近，而不特别地将诸如盖板的附加构件附接到平台。 动叶片冷却通道17c形成在燃气轮机动叶片的内部。 一端与动叶片冷却通路17c连通的冷却连通孔24a，24b与平台5的侧缘附近设置在平台的表面的多个排出口22连通， 通过平台的内部形成。
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公开(公告)号：US09650966B2
公开(公告)日：2017-05-16
申请号：US13977172
申请日：2012-01-31
CPC分类号： F02C9/18 , F01D25/305 , F02C6/08 , F02C7/06 , F02C7/20 , F02C7/268 , F02C9/52 , F05D2220/32 , F05D2250/12 , F05D2260/606 , F05D2270/101
摘要： A gas turbine provided with an air bleeder tube (1) that, during startup, bleeds a portion of the compressed air of a compressor from the compressor and discharged the bled air into a cylindrical exhaust duct (20), wherein the air bleeder tube (1) is disposed at a portion that does not obstruct the flow of the main flow of combustion gas.
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公开(公告)号：US08900512B2
公开(公告)日：2014-12-02
申请号：US13144748
申请日：2010-01-15
申请人： Hiroshi Harada , Tadaharu Yokokawa , Yutaka Koizumi , Toshiharu Kobayashi , Masao Sakamoto , Kyoko Kawagishi , Ikuo Okada , Hidataka Oguma , Taiji Torigoe , Masaki Taneike , Eisaku Ito , Junichiro Masada , Keizo Tsukagoshi , Hidemichi Koyabu
发明人： Hiroshi Harada , Tadaharu Yokokawa , Yutaka Koizumi , Toshiharu Kobayashi , Masao Sakamoto , Kyoko Kawagishi , Ikuo Okada , Hidataka Oguma , Taiji Torigoe , Masaki Taneike , Eisaku Ito , Junichiro Masada , Keizo Tsukagoshi , Hidemichi Koyabu
CPC分类号： F01D5/28 , C22C19/057 , C22F1/00 , C22F1/02 , C22F1/10 , C30B11/00 , C30B29/52 , F05D2300/607 , Y02T50/671
摘要： The Ni-based single crystal alloy disclosed here is a single crystal and has a chemical composition containing, as % by mass, Co: 8 to 12%, Cr: 5 to 7.5%, Mo: 0.2 to 1.2%, W: 5 to 7%, Al: 5 to 6.5%, Ta: 8 to 12%. Hf: 0.01 to 0.2%, Re: 2 to 4%, Si: 0.005 to 0.1%, with the balance of Ni and inevitable impurities.
摘要翻译： 这里公开的Ni系单晶合金为单晶，其化学组成为：Co：8〜12％，Cr：5〜7.5％，Mo：0.2〜1.2％，W：5〜 7％，Al：5〜6.5％，Ta：8〜12％。 Hf：0.01〜0.2％，Re：2〜4％，Si：0.005〜0.1％，余量由Ni和不可避免的杂质构成。
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