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1. 发明授权

US06463729B2 Combined cycle plant with gas turbine rotor clearance control 有权
标题翻译：具有燃气轮机转子间隙控制的联合循环设备
公开(公告)号：US06463729B2
公开(公告)日：2002-10-15
申请号：US09780409
申请日：2001-02-12
申请人： Ryotaro Magoshi , Naoki Hagi , Taku Ichiryu
发明人： Ryotaro Magoshi , Naoki Hagi , Taku Ichiryu
IPC分类号： F02C618
CPC分类号： F01D11/24 , Y02E20/16
摘要： Gas turbine rotor blade tip loss is reduced and loss caused by leakage of working fluid through gap between members constituting an annular flow passage is reduced. Turbine (AT) of a gas turbine (GT) constituting a combined cycle plant (CC) is supported to a turbine casing (4) to be expandable or contractible in turbine shaft (32) radial direction. First blade ring (41) corresponds to first stage turbine stator blades (TS1) and rotor blades (TR1) and comprises a first heating medium flow passage (41P) for steam circulation therein. Second blade ring (42) corresponds to second stage turbine stator blades (TS2) and rotor blades (TR2) and comprises a second heating medium flow passage (42P) for steam circulation therein. Further provided is a communication member (45) for connecting the first blade ring (41) and second blade ring (42) to each other and for communicating the first heating medium flow passage (41P) and second heating medium flow passage (42P) with each other.
摘要翻译：燃气轮机转子叶片尖端损失减小，并且由构成环形流路的构件之间的间隙的工作流体泄漏引起的损失减小。构成联合循环装置（CC）的燃气轮机（GT）的涡轮机（AT）被支撑到涡轮机壳体（4），以在涡轮机轴（32）径向方向上可膨胀或收缩。第一叶片环（41）对应于第一级涡轮机定子叶片（TS1）和转子叶片（TR1），并且包括用于在其中蒸汽循环的第一加热介质流动通道（41P）。第二叶片环（42）对应于第二级涡轮机定子叶片（TS2）和转子叶片（TR2），并且包括用于其中蒸汽循环的第二加热介质流动通道（42P）。还设置有用于将第一叶片环（41）和第二叶片环（42）彼此连接并将第一加热介质流动通道（41P）和第二加热介质流动通道（42P）连通的连通构件（45）彼此。

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

US07340880B2 Compressed air bypass valve and gas turbine 有权
标题翻译：压缩空气旁通阀和燃气轮机
公开(公告)号：US07340880B2
公开(公告)日：2008-03-11
申请号：US10480639
申请日：2002-06-24
申请人： Ryotaro Magoshi , Masaru Nishikatsu
发明人： Ryotaro Magoshi , Masaru Nishikatsu
IPC分类号： F02C9/00 , F23R3/26
CPC分类号： F23R3/045 , F23R3/26 , F23R3/46
摘要： It is the objective of the present invention to enable smooth rotation of the grid plate and normal operation of the bypass valve, regardless of the operational state of the gas turbine. The bypass valve according to the present invention is provided with a frame, which is disposed to cover a plurality of compressed air introduction ports that are arrayed in ring, and in which there are formed a plurality of first openings that communicate with a combustion chamber tail pipe; a grid plate which has a ring shape identical to that formed by the plurality of combustion chamber tail pipes and in which there are formed a plurality of second openings that are positioned opposite the first openings, this grid plate being supported in a manner to enable rotation in its circumferential direction; an inner rail and an outer rail that are provided to the inside surface and the outside surface of the grid plate and are formed in a unitary manner with the frame; and a plurality of guide rollers that are provided to the grid plate, and that come into contact with either the inner rail or the outer rail depending on the circumstances and assist in the rotation of the grid plate.
摘要翻译：本发明的目的是使得格栅的平滑旋转和旁通阀的正常操作，而不管燃气轮机的操作状态如何。根据本发明的旁通阀设置有框架，该框架设置成覆盖排列成环的多个压缩空气引入口，其中形成有多个与燃烧室尾部连通的第一开口管; 格栅板，其具有与由多个燃烧室尾管形成的环形相同的环形，并且其中形成有与第一开口相对定位的多个第二开口，该格栅板以能够旋转的方式被支撑在圆周方向; 内轨道和外轨道，其设置在格板的内表面和外表面上并与框架一体地形成; 以及多个导向辊，其设置在所述格栅板上，并且根据所述情况与所述内轨道或所述外轨道接触，并且有助于所述格栅板的旋转。

4. 发明授权

US07160400B2 Low thermal expansion Ni-base superalloy 有权
标题翻译：低热膨胀Ni基超合金
公开(公告)号：US07160400B2
公开(公告)日：2007-01-09
申请号：US10255716
申请日：2002-09-27
申请人： Ryotaro Magoshi , Hisataka Kawai , Yoshikuni Kadoya , Ryuichi Yamamoto , Toshiharu Noda , Susumu Isobe , Michio Okabe
发明人： Ryotaro Magoshi , Hisataka Kawai , Yoshikuni Kadoya , Ryuichi Yamamoto , Toshiharu Noda , Susumu Isobe , Michio Okabe
IPC分类号： C22C19/05
CPC分类号： C22C1/02 , F22B37/10
摘要： A low thermal expansion Ni-base superalloy contains, by weight % (hereinafter the same as long as not particularly defined) C: 0.15% or less; Si: 1% or less; Mn: 1% or less; Cr: 5 to 20%; at least one of Mo, W and Re of Mo+½(W+Re) of 17 (exclusive) to 25%; Al: 0.2 to 2%; Ti: 0.5 to 4.5%; Fe of 10% or less; at least one of B: 0.02% and Zr: 0.2% or less; a remainder of Ni and inevitable impurities; wherein the atomic % of Al+Ti is 2.5 to 7.0.
摘要翻译：低热膨胀性Ni基超合金含有按重量％计（以下有时没有特别限定）C：0.15％以下; Si：1％以下; Mn：1％以下; Cr：5〜20％; Mo，W和Re的至少一种Mo +½（W + Re）为17（独占）至25％; Al：0.2〜2％ Ti：0.5〜4.5％ 10％以下的Fe; B：0.02％和Zr：0.2％以下中的至少一种; 剩余的Ni和不可避免的杂质; 其中Al + Ti的原子％为2.5〜7.0。

5. 发明授权

US06553766B2 Cooling structure of a combustor tail tube 有权
标题翻译：燃烧器尾管的冷却结构
公开(公告)号：US06553766B2
公开(公告)日：2003-04-29
申请号：US09832937
申请日：2001-04-12
申请人： Takehiko Shimizu , Satoshi Hada , Kouichi Akagi , Katsunori Tanaka , Ryotaro Magoshi , Mitsuo Hasegawa , Shigemi Mandai , Mitsuru Kondo
发明人： Takehiko Shimizu , Satoshi Hada , Kouichi Akagi , Katsunori Tanaka , Ryotaro Magoshi , Mitsuo Hasegawa , Shigemi Mandai , Mitsuru Kondo
IPC分类号： F23R306
CPC分类号： F23M5/08 , F01D9/023 , F02C7/16 , F05D2260/2322 , F23R3/002
摘要： A cooling structure of a combustor tail tube is capable of avoiding the formation of cracks in the tail tube by lessening thermal stress and preventing thermal deformation, thus extending the service life. A multiplicity of cooling jackets (5) extend in the longitudinal direction of the tail tube of a gas turbine combustor along the entire circumference of the tail tube wall. The passage sectional area of the cooling jackets (5) is varied depending on the metal temperature of parts of the tail tube (4). For example, the passage sectional area of the cooling jackets (5) formed at the rotor side wall and the mutually opposite side walls of the adjacent tail tube is larger than the passage sectional area of the cooling jackets (5) formed at the casing side wall.
摘要翻译：燃烧器尾管的冷却结构能够通过减少热应力和防止热变形来避免尾管中的裂纹的形成，延长使用寿命。多个冷却套（5）沿着尾管壁的整个圆周在燃气轮机燃烧器的尾管的纵向方向上延伸。冷却套（5）的通道截面积根据尾管（4）的部件的金属温度而变化。例如，形成在转子侧壁的冷却套（5）和相邻尾管的相对侧壁的通道截面积大于形成在壳体侧的冷却套（5）的通道截面面积壁。

6. 发明授权

US6106766A Material for gas turbine disk 有权
标题翻译：燃气轮机盘材料
公开(公告)号：US6106766A
公开(公告)日：2000-08-22
申请号：US236636
申请日：1999-01-26
申请人： Hisataka Kawai , Yoshikuni Kadoya , Koji Takahashi , Ryotaro Magoshi , Yasuhiko Yasumoto , Tomohiro Tsuchiyama
发明人： Hisataka Kawai , Yoshikuni Kadoya , Koji Takahashi , Ryotaro Magoshi , Yasuhiko Yasumoto , Tomohiro Tsuchiyama
IPC分类号： C22C38/00 , C22C38/44 , C22C38/46 , C22C38/48 , C22C38/54 , F01D5/28
CPC分类号： F01D5/28 , C22C38/001 , C22C38/44 , C22C38/46 , C22C38/48
摘要： A material for a gas turbine disk comprises 0.05 to 0.15 wt % of carbon, 0.10 wt % or less of silicon, 0.40 wt % or less of manganese, 9.0 to 12.0 wt % of chromium, 1.0 to 3.5 wt % of nickel, 0.50 to 0.90 wt % of molybdenum, 1.0 to 2.0 wt % of tungsten, 0.10 to 0.30 wt % of vanadium, 0.01 to 0.10 wt % of niobium, 0.01 to 0.05 wt % of nitrogen, and a remainder comprising iron and unavoidable impurities, wherein the contents of nickel, molybdenum and tungsten satisfy a relationship -1.5 wt %.ltoreq.Mo+W/2-Ni.ltoreq.0.7 wt %. Accordingly, unlike conventional gas turbine disk materials such as a heat resisting steel of 12Cr-type which can be used in an operation at about 400.degree. C., but has reduced toughness and high-temperature creep characteristics in an operation at about 500.degree. C., this material is allowed to have a satisfactory toughness and excellent high-temperature creep characteristics and can be suitably used at high temperatures.
摘要翻译：用于燃气轮机盘的材料包括0.05至0.15重量％的碳，0.10重量％或更少的硅，0.40重量％或更少的锰，9.0至12.0重量％的铬，1.0至3.5重量％的镍，0.50至钼的0.90重量％，钨的1.0〜2.0重量％，钒的0.10〜0.30重量％，铌的0.01〜0.10重量％，氮的0.01〜0.05重量％，余量由铁和不可避免的杂质构成，其中，的镍，钼和钨满足关系-1.5重量％，Mo + W / 2-Ni <0.7重量％。因此，不同于常规的燃气轮机盘材料，例如可在约400℃操作的12Cr型耐热钢，但在约500℃的操作中具有降低的韧性和高温蠕变特性该材料具有令人满意的韧性和优异的高温蠕变特性，并且可以在高温下适当使用。

7. 发明授权

US08083874B2 Method for producing low thermal expansion Ni-base superalloy 有权
标题翻译：生产低热膨胀Ni基超级合金的方法
公开(公告)号：US08083874B2
公开(公告)日：2011-12-27
申请号：US11115159
申请日：2005-04-27
申请人： Shigeki Ueta , Toshiharu Noda , Ryuichi Yamamoto , Yoshikuni Kadoya , Ryotaro Magoshi , Shin Nishimoto
发明人： Shigeki Ueta , Toshiharu Noda , Ryuichi Yamamoto , Yoshikuni Kadoya , Ryotaro Magoshi , Shin Nishimoto
IPC分类号： C22F1/10 , C22C19/05
CPC分类号： C22C19/056 , C22C19/03 , C22C19/057 , C22C19/058 , C22F1/10
摘要： A method for producing a low thermal expansion Ni-base superalloy including the steps of subjecting the alloy to a solution heat treatment under the condition of at a temperature of 1000 to 1200° C. and subjecting the alloy to either a carbide stabilizing treatment for making aggregated carbides on grain boundaries and stabilizing the carbides under the conditions of at a temperature of not less than 850° C. and less than 1000° C. and for 1 to 50 hours, or a carbide stabilizing treatment for making aggregated carbides on grain boundaries and stabilizing the carbides by cooling from the temperature in the solution heat treatment to 850° C. at a cooling rate of 100° C. or less per hour. The method also including the steps of subjecting the alloy to a first aging treatment for precipitating y′ phase under the conditions of at a temperature of 720 to 900° C. and for 1 to 50 hours, and subjecting the alloy to a second aging treatment for precipitating A2B phase under the conditions of at a temperature of 550 to 700° C. and for 5 to 100 hours.
摘要翻译：一种生产低热膨胀Ni基超合金的方法，包括以下步骤：在1000-1200℃的温度下对合金进行固溶热处理，并对合金进行碳化物稳定化处理在不低于850℃，小于1000℃的温度和1〜50小时的条件下，在晶界上凝集的碳化物并使碳化物稳定，或者在晶界上形成碳化碳的碳化物稳定化处理并且通过从固溶热处理中的温度冷却至850℃，以每小时100℃或更低的冷却速度来稳定碳化物。该方法还包括以下步骤：在720至900℃的温度和1至50小时的条件下对合金进行第一时效处理以沉淀y相，并对合金进行第二时效处理用于在550-700℃的温度和5-100小时的条件下沉淀A2B相。

8. 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.

9. 发明授权

US06305902B1 Steam turbine stationary blade 有权
标题翻译：蒸汽轮机固定叶片
公开(公告)号：US06305902B1
公开(公告)日：2001-10-23
申请号：US09422459
申请日：1999-10-21
申请人： Tetsu Konishi , Ryotaro Magoshi , Hideyuki Toda , Takaaki Matsuo , Eiichiro Watanabe
发明人： Tetsu Konishi , Ryotaro Magoshi , Hideyuki Toda , Takaaki Matsuo , Eiichiro Watanabe
IPC分类号： F01D514
CPC分类号： F01D25/32
摘要： Precision cast hollow stationary blade used for final stage of steam turbine is improved to enhance drain recovery efficiency. Hollows (4, 5), sectioned by rib (6) to be independent of each other, are formed in stationary blade (1) passing therethrough from outer shroud 2 to inner shroud 3. A plurality of ventral slits (10 to 20) are provided on blade surface ventral side linearly with predetermined interval between the slits in two parallel rows. Dorsal slits (21 to 26) are also provided linearly with predetermined interval between the slits. Drain on blade surface enters the hollows (5, 4) through the ventral slits (10 to 20) and the dorsal slits (21 to 26), respectively, and flows out of the outer shroud (2) or the inner shroud (3) as drain (40 to 43) to be recovered. While prior art hollow is single hollow and drain entering the hollow through the dorsal slits flows out through the ventral slits or reverse case thereof occurs, the hollows (4, 5) of the present invention being sectioned by the rib (6), the drain is prevented from flowing out to the opposite side.
摘要翻译：用于蒸汽轮机最后阶段的精密铸造中空固定叶片得到改进，以提高排水回收效率。在由外护罩2穿过的固定刀片（1）中形成有由肋（6）分割成彼此独立的空腔（4,5）。多个腹口狭缝（10〜20）在叶片表面腹侧上以两个平行的行之间的狭缝之间的预定间隔线性地设置。背缝狭缝（21至26）也以狭缝间的预定间隔直线地设置。叶片表面上的排水分别通过腹侧缝隙（10〜20）和背缝隙（21〜26）进入中空部（5），并从外护罩（2）或内护罩（3）流出，作为排水（40〜43）进行回收。虽然现有技术的中空是单个中空的，并且通过背面缝隙进入中空的排水通过腹侧狭缝流出或其反向壳体，本发明的中空部分（4,5）由肋（6）分割，排水被防止流出到相对侧。

10. 发明授权

US06302648B1 Steam turbine jointed stationary blade 有权
标题翻译：蒸汽轮机接合固定叶片
公开(公告)号：US06302648B1
公开(公告)日：2001-10-16
申请号：US09427092
申请日：1999-10-26
申请人： Tetsu Konishi , Keizo Tanaka , Hideyuki Toda , Asaharu Matsuo , Toyokazu Kuwana , Ryotaro Magoshi
发明人： Tetsu Konishi , Keizo Tanaka , Hideyuki Toda , Asaharu Matsuo , Toyokazu Kuwana , Ryotaro Magoshi
IPC分类号： F01D900
CPC分类号： F01D9/042 , F01D25/246
摘要： A two stage jointed stationary blade of a high pressure or intermediate pressure steam turbine is formed with a bolt joint in place of a welded joint so as to make detachment and disassembly possible, and thereby facilitating maintenance and inspection work and reducing assembling man-hours. A stationary blade (front stage)(2), outer ring front portion (1) and inner ring front portion (3) are welded into an integral structure. A stationary blade (rear stage) 22, outer ring rear portion (21) and inner ring rear portion (23) are also welded into an integral structure. The outer ring front portion 1, outer ring center portion 10 and the outer ring rear portion 21 are mutually engaged via engaging portions (4, 11 and 12, 24) with precise positioning and then jointed together integrally by bolt (30). The two stage jointed stationary blade can be engaged with moving blades (33, 35), labyrinth seals (32, 34) can be fitted to seal fitting portions (6, 26), and seal fins (31, 34) can be fitted in seal fin grooves (13, 27).
摘要翻译：高压或中压蒸汽轮机的两级接合固定叶片形成有一个螺栓接头代替焊接接头，从而使拆卸和拆卸成为可能，从而便于维护和检查工作，减少组装工时。固定刀片（前台）（2），外环前部（1）和内环前部（3）焊接成一体结构。固定叶片（后台）22，外环后部（21）和内环后部（23）也被焊接成整体结构。外圈前部1，外圈中心部10和外圈后部21通过精确定位的接合部（4,11,12,12）相互接合，然后通过螺栓（30）一体地接合在一起。两级接头固定刀片可与动叶片（33,35）接合，可将迷宫式密封件（32,34）装配到密封配合部分（6,26）上，并将密封翅片（31,34）安装在密封翅片槽（13,27）。

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