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1. 发明授权

US06751962B1 Tail tube seal structure of combustor and a gas turbine using the same structure 有权
标题翻译：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
CPC分类号： F01D9/023 , F23R3/60
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。

2. 发明授权

US06270311B1 Gas turbine split ring 有权
标题翻译：燃气轮机分裂环
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。

3. 发明授权

US6050776A Gas turbine stationary blade unit 有权
标题翻译：燃气轮机固定叶片单元
公开(公告)号：US6050776A
公开(公告)日：2000-04-18
申请号：US152797
申请日：1998-09-14
申请人： Koichi Akagi , Yukihiro Hashimoto , Masahito Kataoka , Yasuoki Tomita , Hiroji Tada
发明人： Koichi Akagi , Yukihiro Hashimoto , Masahito Kataoka , Yasuoki Tomita , Hiroji Tada
IPC分类号： F01D5/22 , F01D9/04 , F01D9/00
CPC分类号： F01D5/22 , F01D9/04 , F05D2230/60
摘要： A gas turbine stationary blade unit in which two stationary blades are formed in a single segment by divided shrouds functions to lessen the occurrence of cracks. Two stationary blades 1a, 1b are fixed to an outer shroud and an inner shroud, respectively. Each shroud is divided into two sections 2a, 2b and 3a, 3b. Flanges 4a, 4b are provided to connect the section together by bolts via boltholes 7. Likewise, flanges 5a, 5b are provided to form a similar connection or joint. If the two stationary blades 1a, 1b are fixed in a single segment by the shrouds which are not divided, a restraining force becomes larger, local stress occurs due to thermal stress and the frequency of crack occurrence increases. However, since the shrouds are divided respectively into two parts and jointed together by bolts, the crack occurrence is lessened. Also, pinholes are provided in opposing faces at the divided portion of the shrouds. Also, pins are inserted into the pinholes for connection of the divided shrouds, thereby relative movement between the divided shrouds is prevented and a strong jointed blade unit is provided.
摘要翻译：一种燃气轮机固定叶片单元，其中两个固定叶片通过分隔的护罩形成在单个段中，起到减少裂缝发生的作用。两个固定叶片1a，1b分别固定在外护罩和内护罩上。每个护罩分为两个部分2a，2b和3a，3b。凸缘4a，4b被设置成通过螺栓通过螺栓孔7将部分连接在一起。同样，凸缘5a，5b被设置成形成类似的连接或接头。如果两个固定叶片1a，1b通过未被分割的护罩固定在单个区段中，则约束力变大，由于热应力而产生局部应力，并且裂纹频率增加。然而，由于护罩被分成两部分并且通过螺栓接合在一起，因此裂纹发生减少。此外，在护罩的分割部分处的相对面中设置针孔。此外，销被插入到针孔中以连接分隔的护罩，从而防止分隔的护罩之间的相对运动，并且提供强的接合的刀片单元。

4. 发明授权

US5957657A Method of forming a cooling air passage in a gas turbine stationary blade shroud 有权
标题翻译：在燃气轮机静叶片护罩中形成冷却空气通道的方法
公开(公告)号：US5957657A
公开(公告)日：1999-09-28
申请号：US145237
申请日：1998-09-01
申请人： Eiji Akita , Masahito Kataoka , Yasuoki Tomita , Wataru Kawai , Takashi Fukura , Hiroshi Asano
发明人： Eiji Akita , Masahito Kataoka , Yasuoki Tomita , Wataru Kawai , Takashi Fukura , Hiroshi Asano
IPC分类号： F01D5/18 , F04D29/38
CPC分类号： F01D5/187 , F05D2240/81
摘要： In a cooling air passage in a gas turbine stationary blade shroud a groove at a shroud end face is formed to extend along the shroud end face. An open portion of the groove is covered by a plug so as to form a cooling air passage. A cooling air passage in which the work accuracy is remarkably enhanced can thus be very easily worked. Preferably the cooling air passage is formed by electric discharge machining (EDM). The same process can be used to form an open portion of the groove, as well as any desired turbulators. The open portion of the groove is closed by a plug which is brazed or welded in place.
摘要翻译：在燃气轮机固定叶片的冷却空气通道中，护罩端面处的槽形成为沿着护罩端面延伸。凹槽的开口部分由塞子覆盖以形成冷却空气通道。因此，能够非常容易地进行作业精度显着提高的冷却风道。优选地，通过放电加工（EDM）形成冷却空气通道。可以使用相同的工艺来形成凹槽的开口部分以及任何所需的湍流器。凹槽的开口部分由钎焊或焊接就位的塞子封闭。

5. 发明授权

US07032386B2 Gas turbine combustor 有权
标题翻译：燃气轮机燃烧器
公开(公告)号：US07032386B2
公开(公告)日：2006-04-25
申请号：US10416515
申请日：2002-06-25
申请人： Shigemi Mandai , Katsunori Tanaka , Masahito Kataoka , Keijirou Saitoh , Wataru Akizuki
发明人： Shigemi Mandai , Katsunori Tanaka , Masahito Kataoka , Keijirou Saitoh , Wataru Akizuki
IPC分类号： F02C1/00 , F23R3/06
CPC分类号： F23R3/04 , F23R2900/03042
摘要： A combustor for a gas turbine has an arrangement to form a layer of cooling-air on an inner surface of a liner of a combustion chamber. This layer of the cooling air extends from a fuel nozzle block of the combustor toward a downstream side with respect to the liner.
摘要翻译：用于燃气轮机的燃烧器具有在燃烧室的衬套的内表面上形成冷却空气层的装置。该冷却空气层从燃烧器的燃料喷嘴块向相对于衬套的下游侧延伸。

6. 发明授权

US06298657B1 Combined cycle power plant generation plant with steam cooling 有权
标题翻译：联合循环发电厂带蒸汽冷却发电厂
公开(公告)号：US06298657B1
公开(公告)日：2001-10-09
申请号：US09693933
申请日：2000-10-23
申请人： Masahito Kataoka , Taku Ichiryu , Yasushi Fukuizumi
发明人： Masahito Kataoka , Taku Ichiryu , Yasushi Fukuizumi
IPC分类号： F02C618
CPC分类号： F02C7/16 , F01K23/10 , Y02E20/16
摘要： In a combined cycle power generation plant in which a gas turbine is cooled by steam, pressure loss of the cooling steam is prevented from increasing and the cooling steam is recovered efficiently. The gas turbine's stationary blade or moving blade is provided with a plurality of mutually independent passages which are arranged in parallel, whereby pressure loss of the cooling steam can be reduced.
摘要翻译：在通过蒸汽冷却燃气轮机的联合循环发电厂中，防止冷却蒸汽的压力损失增加，并且冷却蒸汽被有效地回收。燃气轮机的固定叶片或活动叶片设置有多个相互独立的通道，其平行布置，从而可以降低冷却蒸汽的压力损失。

7. 发明申请

US20070271930A1 Gas turbine having cooling-air transfer system 审中-公开
标题翻译：具有冷却空气传输系统的燃气轮机
公开(公告)号：US20070271930A1
公开(公告)日：2007-11-29
申请号：US11416454
申请日：2006-05-03
申请人： Yoshimasa Takaoka , Masato Araki , Vincent Laurello , Masahito Kataoka , Junichiro Masada , Koichi Ishizaka , Naoki Hagi
发明人： Yoshimasa Takaoka , Masato Araki , Vincent Laurello , Masahito Kataoka , Junichiro Masada , Koichi Ishizaka , Naoki Hagi
IPC分类号： F02C7/12
CPC分类号： F01D5/06 , F01D5/082 , F01D5/084 , F01D5/085 , Y02T50/676
摘要： A gas turbine includes a cooling-air transfer system. The cooing-air transfer system extracts part of air discharged from a compressor to a chamber, and transfers the part of air as cooling air to a rotor disk. The cooling-air transfer system includes a plurality of tubular nozzles independently arranged in a circle inside the chamber to surround a rotor, and a seal disk having seal-disk cooling conduits arranged in a circle around the axis of the rotor so as to receive cooling air ejected from the tubular nozzles. The cooling-air transfer system swirls the cooling air ejected from the tubular nozzles.
摘要翻译：燃气轮机包括冷却空气输送系统。冷凝空气输送系统将从压缩机排出的空气的一部分提取到室，并将作为冷却空气的空气的一部分转移到转子盘。冷却空气传送系统包括多个管状喷嘴，其独立地设置在腔室内的圆周中以围绕转子;以及密封盘，其具有围绕转子轴线布置成圆形的密封盘冷却导管，以便接收冷却从管状喷嘴排出的空气。冷却空气传送系统使从管状喷嘴喷出的冷却空气旋转。

8. 发明授权

US06261058B1 Stationary blade of integrated segment construction and manufacturing method therefor 有权
标题翻译：固定叶片综合分段施工及其制造方法
公开(公告)号：US06261058B1
公开(公告)日：2001-07-17
申请号：US09414394
申请日：1999-10-07
申请人： Masahito Kataoka , Masao Terazaki , Yukihiro Hashimoto
发明人： Masahito Kataoka , Masao Terazaki , Yukihiro Hashimoto
IPC分类号： F01D900
CPC分类号： F01D9/042 , F01D5/288 , F01D9/041 , F05D2230/00 , F05D2230/90 , F05D2240/12 , F05D2260/30 , F05D2300/611
摘要： The present invention provides a stationary blade of integrated segment construction, in which a thermal barrier coating can be applied to the whole blade surface and excessive stress can be avoided in a shroud. A plate seat connector is provided at each end face portion of an inside shroud and an outside shroud attached to outside and inside ends of gas turbine stationary blade. Several stationary blades are integrated by joining the plate seat connectors of the adjacent shrouds by means of bolts and nuts to provide a stationary blade of integrated segment construction.
摘要翻译：本发明提供了一种集成节段结构的固定叶片，其中可以对整个叶片表面施加热障涂层，并且可以避免在护罩中产生过大的应力。在内侧护罩的每个端面部分设置有板座连接器，以及安装在燃气轮机静止叶片的外部和内部端部的外部护罩。通过用螺栓和螺母连接相邻护罩的板座连接器来集成几个固定刀片，以提供一体化段结构的固定刀片。

9. 发明申请

US20100303608A1 Two-shaft gas turbine 审中-公开
标题翻译：双轴燃气轮机
公开(公告)号：US20100303608A1
公开(公告)日：2010-12-02
申请号：US11528690
申请日：2006-09-28
申请人： Masahito Kataoka , Eisaku Ito , Vincent Laurello
发明人： Masahito Kataoka , Eisaku Ito , Vincent Laurello
IPC分类号： F01D1/24
CPC分类号： F01D25/162
摘要： A two-shaft gas turbine includes a high-pressure turbine having an annular gas-passage outlet, a low-pressure turbine having an annular gas-passage inlet, an annular intermediate duct that connects the gas-passage outlet to the gas-passage inlet, a bearing that supports a rotor of the high-pressure turbine and that is attached to a bearing case, and a plurality of struts that support the bearing case. The struts are arranged radially along the circumference of the bearing case so as to extend though the intermediate duct in a space between an outer peripheral surface of the bearing case and an inner peripheral surface of a casing wall that surrounds the intermediate duct. The intermediate duct has strut covers through which the struts extend and which function as first-stage stator blades for the low-pressure turbine.
摘要翻译：双轴燃气轮机包括具有环形气体通道出口的高压涡轮机，具有环形气体通道入口的低压涡轮机，将气体通道出口连接到气体通道入口的环形中间管道支撑高压涡轮机的转子并且附接到轴承箱的轴承以及支撑轴承箱的多个支柱。支柱沿着轴承箱的圆周径向布置，以便在轴承箱的外周表面和围绕中间管的壳体壁的内周表面之间的空间中延伸通过中间管道。中间管道具有支柱盖，支柱通过支柱延伸，并且用作低压涡轮机的第一级定子叶片。

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