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1. 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。

2. 发明授权

US06190130B1 Gas turbine moving blade platform 有权
标题翻译：燃气轮机动叶片平台
公开(公告)号：US06190130B1
公开(公告)日：2001-02-20
申请号：US09255793
申请日：1999-02-23
申请人： Ichiro Fukue , Eiji Akita , Kiyoshi Suenaga , Yasuoki Tomita
发明人： Ichiro Fukue , Eiji Akita , Kiyoshi Suenaga , Yasuoki Tomita
IPC分类号： F01D518
CPC分类号： F01D5/187 , F05D2240/81
摘要： A gas turbine moving blade platform having a simplified platform cooling structure. A cooling effect of the platform side end portions is increased resulting in uniform cooling of the entire platform. Cooling passages (2, 3) are bored in the platform (1) front portion so as to communicate with a cooling air passage (52) of the moving blade (51) and open at both platform side end surfaces. The openings are closed by inserting covers (2a, 2b) therein. Cooling passages (6, 4) are bored in platform (1) side end portions so as to communicate with the front end cooling passages (2, 3), respectively, and open in the platform rear end surface. A plurality of cooling holes (5) are bored so as to communicate with the cooling passage (4) and open at the platform side end surface. Thus, the entire platform is cooled uniformly and the platform side portions are cooled by the cooling holes (5) so that an effective cooling performance is ensured and also the workability of the cooling lines is enhanced.
摘要翻译：具有简化的平台冷却结构的燃气轮机动叶片平台。平台侧端部的冷却效果增加，导致整个平台的均匀冷却。在平台（1）的前部分中钻出冷却通道（2,3），以便与活动叶片（51）的冷却空气通道（52）连通并在两个平台侧端面处打开。通过将盖（2a，2b）插入其中来封闭开口。平台（1）的侧端部分分别将冷却通道（6,4）与前端冷却通道（2,3）连通，并在平台后端面开口。多个冷却孔（5）钻孔，以与冷却通道（4）连通并在平台侧端面打开。因此，整个平台被均匀地冷却，并且平台侧部分被冷却孔（5）冷却，从而确保了有效的冷却性能，并且还提高了冷却管线的可加工性。

3. 发明授权

US6152695A Gas turbine moving blade 有权
标题翻译：燃气轮机动叶片
公开(公告)号：US6152695A
公开(公告)日：2000-11-28
申请号：US243821
申请日：1999-02-03
申请人： Ichiro Fukue , Eiji Akita , Kiyoshi Suenaga , Yasuoki Tomita
发明人： Ichiro Fukue , Eiji Akita , Kiyoshi Suenaga , Yasuoki Tomita
IPC分类号： F01D5/18 , F01D5/20 , F01D5/22
CPC分类号： F01D5/187 , F01D5/225 , F05D2240/81 , F05D2260/22141
摘要： In a gas turbine moving blade 1, the convection of cooling air is promoted to enhance the heat transfer rate, the cooling effect of a shroud 2 is enhanced and the entire cooling effect of the blade is enhanced. An inner cavity 10 is formed in the blade over the entire length thereof. A multiplicity of pin fins 5 are provided in the inner cavity, being fixed to wall thereof. An enlarged cavity 6 is formed in the shroud 2 of a terminal end of the blade 1. Cooling air entering the inner cavity 10 of the blade 1 flows into the enlarged cavity 6 and flows out of the shroud 2 downwardly through holes 7 of a peripheral portion of the enlarged cavity 6. The entire portion of the shroud 2 is cooled uniformly, and the cooling effect of the entire blade is enhanced by an enhanced heat transfer rate in the blade and by uniform cooling of the entire shroud.
摘要翻译：在燃气轮机动叶片1中，促进冷却空气的对流，提高传热速度，提高护罩2的冷却效果，提高叶片的整体冷却效果。在叶片的整个长度上形成内腔10。多个销翅片5设置在内腔中，固定在其壁上。在叶片1的末端的护罩2中形成有扩大的空腔6.进入叶片1的内腔10的冷却空气流入扩大空腔6，并通过周边的孔7向下流出护罩2 扩大的腔体6的部分。护罩2的整个部分被均匀地冷却，并且整个刀片的冷却效果通过增加叶片中的传热速率和整个护罩的均匀冷却来增强。

4. 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。

5. 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。

6. 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。

7. 发明授权

US07481614B2 Moving blade and gas turbine using the same 有权
标题翻译：使用相同的叶片和燃气轮机
公开(公告)号：US07481614B2
公开(公告)日：2009-01-27
申请号：US11059644
申请日：2005-02-17
申请人： Yasuoki Tomita , Masaki Ono , Eiji Akita , Masao Terazaki , Masayuki Takahama , Kouji Watanabe , Hideki Murata
发明人： Yasuoki Tomita , Masaki Ono , Eiji Akita , Masao Terazaki , Masayuki Takahama , Kouji Watanabe , Hideki Murata
IPC分类号： F01D5/14
CPC分类号： F01D11/006 , F01D5/22 , F01D11/008
摘要： In a gas turbine having a plurality of moving blades provided on a rotary shaft in a circumferentially adjoining condition, a seal pin is provided in a spacing between the shanks of the adjacent moving blades for preventing leakage of cooling air from a blade root portion side to an airfoil side; an arcuately depressed portion is formed on the shank of each of the moving blades; and vibration of each of the moving blades is suppressed in such a manner that the seal pin serves as a spring system while the airfoil portion, the platform, the shank, and the blade root portion serve as a mass system.
摘要翻译：在具有沿周向邻接状态设置在旋转轴上的多个动叶片的燃气轮机中，密封销以相邻的动叶片的柄之间的间隔设置，用于防止冷却空气从叶片根部侧泄漏到机翼一侧在每个动叶片的柄部上形成弓形凹陷部分; 并且以这样一种方式抑制每个动叶片的振动，使得当翼型部分，平台，柄部和叶片根部部分用作质量系统时，密封销用作弹簧系统。

8. 发明授权

US6099253A Gas turbine rotor blade 有权
标题翻译：燃气轮机转子叶片
公开(公告)号：US6099253A
公开(公告)日：2000-08-08
申请号：US203680
申请日：1998-12-01
申请人： Ichiro Fukue , Eiji Akita , Kiyoshi Suenaga , Yasuoki Tomita
发明人： Ichiro Fukue , Eiji Akita , Kiyoshi Suenaga , Yasuoki Tomita
IPC分类号： F01D5/18 , F01D5/20 , F02C7/18
CPC分类号： F01D5/225 , F01D5/187 , Y02T50/676
摘要： A gas turbine rotor blade has a plurality of first cooling holes for the flow of a cooling gas bored in a blade portion along its lengthwise direction and a plurality of second cooling holes for flow of the cooling gas bored in a shroud along its plane direction so as to communicate with the first cooling holes, and is constructed such that the cooling gas can flow in a uniform distribution. The plurality of the first cooling holes 3 for flow of the cooling gas are bored in the blade portion 2 and the plurality of the second cooling holes 5 for flow of the cooling gas are bored in the shroud 1 along its plane direction. The second cooling holes 5 communicate with the first cooling holes 3, hole to hole, via two-step holes 4, and the second cooling holes 5 are bored alternately on the dorsal side and the ventral side of the rotor blade.
摘要翻译：燃气轮机转子叶片具有多个第一冷却孔，用于沿其长度方向在叶片部分中钻出的冷却气体的流动，以及多个用于沿着其平面方向在护罩中钻出的冷却气体的流动的第二冷却孔，与第一冷却孔连通，并且被构造成使得冷却气体能够以均匀的分布流动。多个用于冷却气体流动的第一冷却孔3在叶片部分2中钻孔，并且用于冷却气体流动的多个第二冷却孔5沿其平面方向在护罩1中钻孔。第二冷却孔5通过两步孔4与第一冷却孔3，孔对孔连通，第二冷却孔5在转子叶片的背侧和腹侧交替地钻孔。

9. 发明授权

US6071075A Cooling structure to cool platform for drive blades of gas turbine 失效
标题翻译：燃气轮机驱动叶片冷却平台冷却结构
公开(公告)号：US6071075A
公开(公告)日：2000-06-06
申请号：US28886
申请日：1998-02-24
申请人： Yasuoki Tomita , Eiji Akita , Masao Terazaki
发明人： Yasuoki Tomita , Eiji Akita , Masao Terazaki
IPC分类号： F01D5/08 , F01D5/18 , F01D5/30 , F02C7/18
CPC分类号： F01D5/187 , F05D2240/81 , F05D2260/2212
摘要： A mechanism for cooling the platform for the drive blades of a gas turbine uses a simple configuration which reliably cools the platform. The mechanism includes cooling channels in the interior of the platform which open out from one of the cooling air channels for cooling the turbine blades and which exit the platform through the edge nearest the tail. Cooling channels in the platform open out from the entrance to blade cooling channels, travel from the head of the blade along the blade sides, and exit through the edge near the tail of the blade. This structure diverts a portion of the cooling air entering the blade from the cooling channel in the base in order to cool the platform. Cooling air channels may extend from an enclosed air space below the platform to the upper surface of the platform at the front or rear side of the blade. Air channels may also extend on the rear of the turbine blade obliquely from the underside of the platform to the trailing edge of the platform. These channels or combinations thereof constitute a cooling structure through which air can flow to cool a platform for the drive blades of a gas turbine in an efficient and effective manner.
摘要翻译：用于冷却燃气轮机的驱动叶片的平台的机构使用可靠地冷却平台的简单构造。该机构包括平台内部的冷却通道，其从一个冷却空气通道开口，用于冷却涡轮叶片，并且通过最靠近尾部的边缘离开平台。平台上的冷却通道从入口到叶片冷却通道开口，沿着叶片侧从叶片的头部行进，并通过靠近叶片尾部的边缘离开。这种结构将进入叶片的冷却空气的一部分从基座中的冷却通道转移，以便冷却平台。冷却空气通道可以从平台下方的封闭空气空间延伸到在叶片的前侧或后侧的平台的上表面。空气通道也可以在涡轮叶片的后部从平台的下侧向平台的后边缘倾斜延伸到平台的后缘。这些通道或其组合构成了一种冷却结构，通过该冷却结构，空气可以以有效和有效的方式流动以冷却燃气轮机的驱动叶片的平台。

10. 发明授权

US6065282A System for cooling blades in a gas turbine 失效
标题翻译：用于在燃气轮机中冷却叶片的系统
公开(公告)号：US6065282A
公开(公告)日：2000-05-23
申请号：US960466
申请日：1997-10-29
申请人： Ichiro Fukue , Eiji Akita , Yasuoki Tomita
发明人： Ichiro Fukue , Eiji Akita , Yasuoki Tomita
IPC分类号： F02C7/18 , F02G3/00 , F02C5/00
CPC分类号： F02C7/185 , F05D2260/205
摘要： A gas turbine comprises: a first closed circuit in which cooling gas is supplied to a casing, allowed to pass through stationary blades, and removed to the outside of casing after cooling the stationary blades; a second closed circuit in which cooling air is supplied to the casing, allowed to pass through moving blades, and removed to the outside of casing after cooling the moving blades; a cooler for cooling the cooling gas in the first and second closed circuits; and a booster for pressurizing and circulating the cooling gas cooled by the cooler.Also, A gas turbine comprises: a first closed circuit in which cooling air cooled after being extracted from a combustor plenum is allowed to pass through stationary blades successively to cool the stationary blades, and then recovered and returned to a compressor on the upstream side of the combustor plenum; and a second closed circuit in which cooling air cooled after being extracted from the combustor plenum is allowed to pass through moving blades successively to cool the moving blades, and then recovered and returned to the compressor.
摘要翻译：燃气轮机包括：第一闭合回路，其中冷却气体被供给到壳体，允许其通过固定叶片，并且在冷却固定叶片之后被移除到壳体外部; 第二闭合回路，其中冷却空气被供给到壳体，允许通过动叶片，并且在冷却动叶片之后被移除到壳体外部; 用于冷却第一和第二闭合回路中的冷却气体的冷却器; 以及用于对由冷却器冷却的冷却气体进行加压和循环的增压器。此外，A燃气轮机包括：第一闭合回路，其中在从燃烧室增压室抽出之后冷却的冷却空气被允许依次通过固定叶片以冷却固定叶片，然后回收并返回到压缩机的上游侧燃烧室增压室; 以及第二闭合回路，其中冷却从冷却室抽出的冷却空气被连续通过运动叶片以冷却动叶片，然后回收并返回压缩机。

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