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1. 发明申请

US20100226791A1 BLADE COOLING STRUCTURE OF GAS TURBINE 有权
标题翻译：气体涡轮叶片冷却结构
公开(公告)号：US20100226791A1
公开(公告)日：2010-09-09
申请号：US12670912
申请日：2007-08-30
申请人： Daigo Fujimura , Hideaki Sugishita , Masaaki Matsuura , Hiroyuki Yamamoto , Shunsuke Torii , Satoshi Hada , Kiyoshi Suenaga , Yuko Suenaga
发明人： Daigo Fujimura , Hideaki Sugishita , Masaaki Matsuura , Hiroyuki Yamamoto , Shunsuke Torii , Satoshi Hada , Kiyoshi Suenaga , Yuko Suenaga
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F05D2240/127 , F05D2250/185 , F05D2260/2212 , F05D2260/22141 , Y02T50/676
摘要： A blade cooling structure of a gas turbine, which can reduce the pressure loss of a cooling medium without decreasing the heat transfer coefficient, is provided. The blade cooling structure comprises a cooling passage (15) for flowing cooling air (A) from a proximal end portion (12) toward a blade portion (14) of a moving blade (11), a plurality of turbulators (21) arranged, on both wall surfaces of the cooling passage (15) opposing each other, in such a manner as to be inclined with respect to the flowing direction of the cooling air (A), and a plurality of dimples (22) formed in a downstream region (N) downstream of a center position (O) in the flowing direction of the cooling air (A) on the wall surface of the cooling passage (15) between the adjacent turbulators (21).
摘要翻译：提供了一种燃气轮机的叶片冷却结构，其可以在不降低传热系数的情况下降低冷却介质的压力损失。叶片冷却结构包括用于使冷却空气（A）从基端部（12）朝向活动叶片（11）的叶片部分（14）流动的冷却通道（15），多个湍流器（21）在相对于冷却空气（A）的流动方向倾斜的方式相互相对的冷却通路（15）的两壁面上形成有多个凹部（22），形成在下游区域（N）在冷却空气（A）的流动方向上在相邻的湍流器（21）之间的冷却通道（15）的壁表面上的中心位置（O）的下游。

2. 发明授权

US08556583B2 Blade cooling structure of gas turbine 有权
标题翻译：燃气轮机叶片冷却结构
公开(公告)号：US08556583B2
公开(公告)日：2013-10-15
申请号：US12670912
申请日：2007-08-30
申请人： Daigo Fujimura , Hideaki Sugishita , Masaaki Matsuura , Hiroyuki Yamamoto , Shunsuke Torii , Satoshi Hada , Kiyoshi Suenaga , Yuko Suenaga
发明人： Daigo Fujimura , Hideaki Sugishita , Masaaki Matsuura , Hiroyuki Yamamoto , Shunsuke Torii , Satoshi Hada , Kiyoshi Suenaga , Yuko Suenaga
IPC分类号： B64C11/24
CPC分类号： F01D5/187 , F05D2240/127 , F05D2250/185 , F05D2260/2212 , F05D2260/22141 , Y02T50/676
摘要： A blade cooling structure of a gas turbine, which can reduce the pressure loss of a cooling medium without decreasing the heat transfer coefficient, is provided. The blade cooling structure comprises a cooling passage (15) for flowing cooling air (A) from a proximal end portion (12) toward a blade portion (14) of a moving blade (11), a plurality of turbulators (21) arranged, on both wall surfaces of the cooling passage (15) opposing each other, in such a manner as to be inclined with respect to the flowing direction of the cooling air (A), and a plurality of dimples (22) formed in a downstream region (N) downstream of a center position (O) in the flowing direction of the cooling air (A) on the wall surface of the cooling passage (15) between the adjacent turbulators (21).
摘要翻译：提供了一种燃气轮机的叶片冷却结构，其可以在不降低传热系数的情况下降低冷却介质的压力损失。叶片冷却结构包括用于使冷却空气（A）从基端部（12）朝向活动叶片（11）的叶片部分（14）流动的冷却通道（15），多个湍流器（21）在相对于冷却空气（A）的流动方向倾斜的方式相互相对的冷却通路（15）的两壁面上形成有多个凹部（22），形成在下游区域（N）在冷却空气（A）的流动方向上在相邻的湍流器（21）之间的冷却通道（15）的壁表面上的中心位置（O）的下游。

3. 发明授权

US07596947B2 Gas turbine plant 失效
标题翻译：燃气轮机厂
公开(公告)号：US07596947B2
公开(公告)日：2009-10-06
申请号：US10590014
申请日：2004-12-22
申请人： Noboru Yanai , Yoshiaki Tsukuda , Hideaki Sugishita , Satoru Kamohara
发明人： Noboru Yanai , Yoshiaki Tsukuda , Hideaki Sugishita , Satoru Kamohara
IPC分类号： G21D5/00
CPC分类号： G21D5/00 , F02C1/05 , F02C1/10 , F02C3/10 , F02C9/18 , F05D2220/76 , F05D2260/85 , G21C1/07 , G21D1/02 , Y02E30/36
摘要： A gas turbine plant, wherein a plurality of first gas turbines positioned coaxially with compressors and a second gas turbine positioned coaxially with a generator are rotated by a coolant heated by heat energy provided by the fission of a coated particle fuel. A flow in a bypass passage is controlled by controlling the opening of bypass valves of (n−1) in quantity which bypass the first gas turbines on up to (n−1) shafts in starting. Accordingly, the rotational speeds of the first gas turbines on up to (n) shafts are increased to a rated rotational speed in order starting at the initial stage on the upstream side of a high temperature gas-cooled reactor toward the lower stage for each shaft.
摘要翻译：一种燃气轮机设备，其中与压缩机同轴定位的多个第一燃气轮机和与发电机同轴设置的第二燃气轮机由被涂覆颗粒燃料的裂变所提供的热能加热的冷却剂旋转。旁通通道中的流动通过控制（n-1）的旁通阀的开启量来控制，该旁路阀在启动时绕过多达（n-1）个轴上的第一燃气轮机的数量。因此，将高达（n）个轴上的第一燃气轮机的旋转速度提高到额定转速，从而在高温气冷式反应器的上游侧的初始阶段开始朝向每个轴的下段。

4. 发明申请

US20070183554A1 Gas turbine plant 审中-公开
标题翻译：燃气轮机厂
公开(公告)号：US20070183554A1
公开(公告)日：2007-08-09
申请号：US10590012
申请日：2004-12-22
申请人： Noboru Yanai , Yoshiaki Tsukuda , Hideaki Sugishita , Satoru Kamohara
发明人： Noboru Yanai , Yoshiaki Tsukuda , Hideaki Sugishita , Satoru Kamohara
IPC分类号： G21C7/32
CPC分类号： F02C1/05 , F02C1/10 , F02C9/18 , F05D2220/76 , G21D5/06
摘要： A gas turbine plant, wherein a first gas turbine positioned coaxially with a compressor and a second gas turbine positioned coaxially with a generator are rotated by a coolant heated by heat energy provided by the fission of a coated particle fuel. The rotational speed of the first gas turbine is controlled by controlling a flow in the bypass passage of the second gas turbine.
摘要翻译：一种燃气轮机设备，其中与压缩机同轴地定位的第一燃气轮机和与发电机同轴设置的第二燃气轮机由被涂覆颗粒燃料的裂变所提供的热能加热的冷却剂旋转。通过控制第二燃气轮机的旁路通道中的流量来控制第一燃气轮机的转速。

5. 发明授权

US06533542B2 Split ring for gas turbine casing 有权
公开(公告)号：US06533542B2
公开(公告)日：2003-03-18
申请号：US10043201
申请日：2002-01-14
申请人： Hideaki Sugishita , Hisato Arimura , Yasuoki Tomita
发明人： Hideaki Sugishita , Hisato Arimura , Yasuoki Tomita
IPC分类号： F01D1108
CPC分类号： F01D9/04 , F01D5/145
摘要： A split ring is disposed on an inner wall of a gas turbine casing. The split ring is composed of a plurality of split segments that are arranged on the inner wall of the casing in circumferential direction. A predetermined clearance is formed between the inner face of a split segment and the rotor blade tips. The split segments are arranged so that a predetermined circumferential clearance is formed between the split segments in order to allow the thermal expansion of the segments. A circumferential end face located upstream side of the segments with respect to the direction of the rotor blade rotation is connected to the inner face by a transition face having a surface formed as an inclined plane. The inclined plane prevents the swirl flow caused by the rotating rotor blade from impinging the upstream end face and, thereby, suppresses a temperature rise of the split segment at the upstream end face.

6. 发明授权

US6109019A Steam cooled gas turbine system 失效
标题翻译：蒸汽式燃气轮机系统
公开(公告)号：US6109019A
公开(公告)日：2000-08-29
申请号：US31677
申请日：1998-02-27
申请人： Hideaki Sugishita
发明人： Hideaki Sugishita
IPC分类号： F01D5/18 , F01D9/02 , F01K23/10 , F02C7/18 , F02C6/18 , F02C7/12
CPC分类号： F01K23/106 , F05B2260/233 , Y02E20/16
摘要： A steam cooled gas turbine system in a combined power plant, constituted such that a tail pipe of a combustor is cooled with intermediate pressure steam from an exhaust heat recovery boiler, or outlet bleed steam from a high pressure turbine, and the cooling steam is recovered into an intermediate pressure turbine or an intermediate area of a reheater of the exhaust heat recovery boiler, whereby thermal efficiency is improved, and a cut in NO.sub.x is achieved.
摘要翻译：一种组合动力装置中的蒸汽冷却燃气轮机系统，其构造成使得燃烧器的尾管由来自废热回收锅炉的中压蒸汽或来自高压涡轮机的出口排出蒸汽冷却，并且冷却蒸汽被回收进入废热回收锅炉的中压涡轮机或再热器的中间区域，从而提高热效率，并实现NOx的切断。

7. 发明授权

US6098398A Low temperature hydrogen combustion turbine 失效
标题翻译：低温氢燃气轮机
公开(公告)号：US6098398A
公开(公告)日：2000-08-08
申请号：US31679
申请日：1998-02-27
申请人： Kazuo Uematsu , Hidetaka Mori , Hideaki Sugishita , Herbert Jericha
发明人： Kazuo Uematsu , Hidetaka Mori , Hideaki Sugishita , Herbert Jericha
IPC分类号： F01K7/38 , F01K7/44 , F01K25/00 , F02C1/00 , F02C1/04 , F02C3/22 , F02C3/30 , F02C3/34 , F02C6/02 , F02C7/141 , F02C6/18
CPC分类号： F02C3/22 , F01K25/005 , F02C1/007 , F02C1/04 , F02C3/34 , F02C6/02
摘要： In a hydrogen combustion turbine plant employing a topping bleed cycle, a low temperature hydrogen combustion turbine bleeds part of exhaust from a third turbine to cool a first turbine, thereby achieving a high efficiency in a desired temperature range while curtailing a cost increase without involving the addition of accessory instruments.
摘要翻译：在使用顶部排放循环的氢燃烧涡轮机设备中，低温氢燃烧涡轮机从第三涡轮机排出一部分排气以冷却第一涡轮机，从而在期望的温度范围内实现高效率，同时降低成本增加而不涉及添加附件仪器。

8. 发明授权

US5809768A Hydrogen-oxygen combustion turbine plant 失效
标题翻译：氢氧燃气轮机厂
公开(公告)号：US5809768A
公开(公告)日：1998-09-22
申请号：US833690
申请日：1997-04-08
申请人： Kazuo Uematsu , Hidetaka Mori , Hideaki Sugishita
发明人： Kazuo Uematsu , Hidetaka Mori , Hideaki Sugishita
IPC分类号： F01K25/00 , F02C3/22 , F02C3/34 , F03C3/22
CPC分类号： F02C3/34 , F01K25/005 , F02C3/22 , F05D2260/212 , Y02E20/16
摘要： A hydrogen-oxygen combustion turbine plant having an improved thermal efficiency and capable of being designed in a flexible manner. The plant is constructed as follows. A compressor is divided into a plurality of units (1A and 1B), a water injection device (14) is disposed between the compressor units, and exhaust water from a condenser (10) of a second turbine (6) is utilized as a water supply. A gas turbine is also divided into a plurality of units (3A to 3C) with multiple axes. Further, not only extracted steam (9A and 9B) from the compressors (1A and 1B) but also the extracted steam (12A and 12B) from the second turbine (6) and the extracted steam (13A and 13B) from the exhaust of the third turbine (8) are used as cooled steam for gas turbines (3A to 3C) and the combustion chamber (2).
摘要翻译：一种具有改善热效率并能灵活设计的氢氧燃烧涡轮机组。该植物的构造如下。压缩机被分成多个单元（1A和1B），在压缩机单元之间设置注水装置（14），并且将来自第二涡轮（6）的冷凝器（10）的废水用作水供应。燃气轮机也被分成具有多个轴的多个单元（3A至3C）。此外，不仅从压缩机（1A和1B）提取蒸汽（9A和9B），而且从第二涡轮机（6）提取的蒸汽（12A和12B）和提取的蒸汽（13A和13B）第三涡轮（8）用作燃气轮机（3A至3C）和燃烧室（2）的冷却蒸汽。

9. 发明授权

US06679047B1 Combined cycle gas turbine system 有权
公开(公告)号：US06679047B1
公开(公告)日：2004-01-20
申请号：US09963509
申请日：2001-09-27
申请人： Kazuo Uematsu , Yoshinori Hyakutake , Hideaki Sugishita
发明人： Kazuo Uematsu , Yoshinori Hyakutake , Hideaki Sugishita
IPC分类号： F02C618
CPC分类号： F01K23/106 , F02C7/16 , F05D2260/2322 , Y02E20/16
摘要： A combined cycle gas turbine system is improved to enhance a gas turbine efficiency and a combined efficiency by effecting steam-cooling of a combustor transition piece and a turbine blade. The combined cycle system has a gas turbine (8) having a generator (1), a compressor (2), a combustor (3), a blade cooling air cooler (4) and a turbine (6), a steam turbine (29) having a high pressure turbine (21), an intermediate pressure turbine (22) and a low pressure turbine (23), and a waste heat recovery boiler (9). Saturated water of a high pressure pump (27) is partially led into a demineralizer (118) and a water sprayer (116) for cooling steam to be supplied into a moving blade (52). The steam, after being used for cooling, is recovered into a reheater (20). Outlet steam of the high pressure turbine (21) is led into a stationary blade (53) for cooling thereof and the steam is then recovered into an inlet of the intermediate pressure turbine (22). Also, steam of an intermediate pressure superheater (16) is led into a combustor transition piece (54) for cooling thereof and the steam is recovered into the inlet of the intermediate pressure turbine (22). Thus, moving blade cooling steam is reduced and the combined efficiency is enhanced.

10. 发明授权

US06536205B2 Combined cycle power plant 失效
公开(公告)号：US06536205B2
公开(公告)日：2003-03-25
申请号：US10096939
申请日：2002-03-14
申请人： Hideaki Sugishita , Hidetaka Mori , Ichiro Fukue , Kazuo Uematsu
发明人： Hideaki Sugishita , Hidetaka Mori , Ichiro Fukue , Kazuo Uematsu
IPC分类号： F02C618
CPC分类号： F01K23/10 , Y02E20/16 , Y02E20/344
摘要： Provided is turbine plant using methanol as fuel in which working fluid is compressed by compressor 1 and led into combustor 2. A mixture of H2 and CO2 as fuel added with O2 is burned to generate high temperature gas, which works at high temperature turbine 3, flows through heat exchangers 4, 5 and returns partly to the compressor 1 and enters partly low pressure turbine 7 of bottoming system to work. Condensed water from condenser 9 of the bottoming system is pressurized by pressure pump 10 and flows through the heat exchangers 4, 5 to become high temperature steam and to work at high pressure turbine 6. Exhaust gas thereof is mixed into the combustor 2. A mixture of methanol and water is supplied into reformer 13 to absorb heat from the heat exchanger 4 to be reformed into H2 and CO2, which is supplied into the combustor 2. A high temperature portion of the high temperature turbine 3 is cooled by cooling medium extracted from compressor 1 outlet and high pressure turbine 6 outlet thereby reliability of the high temperature turbine 3 is enhanced.

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