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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：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：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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公开(公告)号：US20140023493A1
公开(公告)日：2014-01-23
申请号：US14008434
申请日：2012-03-22
申请人： Hitoshi Kitagawa , Yasuro Sakamoto , Eisaku Ito
发明人： Hitoshi Kitagawa , Yasuro Sakamoto , Eisaku Ito
IPC分类号： F01D9/02
CPC分类号： F01D9/02 , F01D25/30 , F02C7/00 , F05D2250/52 , F05D2260/213
摘要： In a turbine exhaust structure and a gas turbine, a turbine casing (26) formed in an annular shape to constitute a combustion gas passage A is provided. An exhaust diffuser (31) formed in an annular shape to constitute a flue gas passage (B) is connected to the turbine casing (26) to constitute a configuration. By providing a pressure loss body (61) in the exhaust diffuser (31), efficient pressure recovery can be carried out, which improves turbine efficiency, thereby enabling improvement of the performance.
摘要翻译： 在涡轮机排气结构和燃气轮机中，设置形成为环状的涡轮机壳体（26），构成燃烧气体通路A. 形成为构成烟道气体通路（B）的环状的排气扩散器（31）与涡轮机壳体（26）连接构成。 通过在排气扩散器（31）中设置压力损失体（61），可以进行有效的压力恢复，提高了涡轮效率，从而能够提高性能。
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8.发明申请THERMAL BARRIER COATING MATERIAL, THERMAL BARRIER COATING, TURBINE MEMBER, AND GAS TURBINE 审中-公开热障涂层材料，热障涂层，涡轮部件和气体涡轮公开(公告)号：US20110262770A1
公开(公告)日：2011-10-27
申请号：US13125897
申请日：2009-11-27
申请人： Taiji Torigoe , Ichiro Nagano , Ikuo Okada , Keizo Tsukagoshi , Koji Takahashi , Yoshifumi Okajima , Soji Kasumi , Eisaku Ito , Kazutaka Mori
发明人： Taiji Torigoe , Ichiro Nagano , Ikuo Okada , Keizo Tsukagoshi , Koji Takahashi , Yoshifumi Okajima , Soji Kasumi , Eisaku Ito , Kazutaka Mori
CPC分类号： C04B35/486 , C04B2235/3224 , C04B2235/96 , C04B2235/9607 , C23C4/04 , C23C4/11 , C23C28/3215 , C23C28/345 , C23C28/3455 , F01D5/288 , F05D2230/90 , Y10T428/12618
摘要： A thermal barrier coating material that exhibits superior high-temperature crystal stability to YSZ, as well as a high degree of toughness and an excellent thermal barrier effect. Also provided are a thermal barrier coating, which has a ceramic layer formed using the thermal barrier coating material and exhibits excellent durability to heat cycling, and a turbine member and a gas turbine which are each provided with the thermal barrier coating. The thermal barrier coating material comprises mainly ZrO2 which contains Yb2O3 and Sm2O3 as stabilizers, wherein the amount of the stabilizers is not less than 2 mol % and not more than 7 mol %, and the amount of the Sm2O3 is not less than 0.1 mol % and not more than 2.5 mol %.
摘要翻译： 对YSZ显示优异的高温晶体稳定性以及高韧性和优异的热障效果的热障涂层材料。 还提供了一种隔热涂层，其具有使用该热障涂层材料形成的陶瓷层，并显示出优异的热循环耐久性，以及每个设置有该热障涂层的涡轮机构件和燃气轮机。 热障涂层材料主要包含含有Yb2O3和Sm2O3作为稳定剂的ZrO 2，其中稳定剂的量不小于2mol％且不大于7mol％，并且Sm2O3的量不小于0.1mol％ 不超过2.5摩尔％。
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公开(公告)号：US07229248B2
公开(公告)日：2007-06-12
申请号：US10913366
申请日：2004-08-09
申请人： Eisaku Ito , Eiji Akita
发明人： Eisaku Ito , Eiji Akita
IPC分类号： F01D1/02
CPC分类号： F01D5/142 , F01D5/141 , F01D5/145 , F05D2240/12
摘要： In the blade structure in a gas turbine, front-edge including angles are made large. As a result, a curve of a relative relationship between incidence angles ic1 and is1 and pressure loss becomes mild. Entrance metal angles are made small. As a result, it becomes possible to make the incidence angles small. Chord length of a tip portion of a moving blade is made large. As a result, it becomes possible to make small the deceleration on a rear surface of the tip portion of the moving blade. Accordingly, it becomes possible to make the pressure loss small, and therefore, it becomes possible to improve the turbine efficiency.
摘要翻译： 在燃气轮机的叶片结构中，使包括角度在内的前缘变大。 结果，入射角度ic 1之间的相对关系曲线为1，压力损失变得温和。 入口金属角度很小。 结果，可以使入射角变小。 活动叶片的尖端部分的弦长变大。 结果，能够使动叶片的前端部的后表面的减速度变小。 因此，可以使压力损失小，能够提高涡轮效率。
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公开(公告)号：US06779973B2
公开(公告)日：2004-08-24
申请号：US10002089
申请日：2001-12-06
申请人： Eisaku Ito , Kazuo Uematsu
发明人： Eisaku Ito , Kazuo Uematsu
IPC分类号： F01D900
CPC分类号： F01D5/142 , F01D5/141 , F01D5/143 , F01D5/145 , F01D5/16 , F01D25/30 , F05D2210/30 , F05D2210/31 , F05D2240/301 , F05D2250/292 , F05D2250/70 , Y02T50/673 , Y10S416/02
摘要： The pressure ratio &Dgr;P4S of a final stage moving blade is reduced. As a result, the Mach number in the final stage moving blade can be suppressed, and in the gas turbine operating at a pressure ratio of 20 or more, therefore, decline of turbine efficiency due to shock wave loss can be prevented securely.
摘要翻译： 最终级动叶片的压力比DeltaP4S减小。 结果，可以抑制最终级动叶片中的马赫数，并且在以20以上的压力比工作的燃气轮机中，可以可靠地防止由于冲击波损耗引起的涡轮效率的下降。
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