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21. 发明授权

US5915923A Gas turbine moving blade 失效
标题翻译：燃气轮机动叶片
公开(公告)号：US5915923A
公开(公告)日：1999-06-29
申请号：US861753
申请日：1997-05-22
申请人： Yasuoki Tomita , Taku Ichiryu , Kiyoshi Suenaga
发明人： Yasuoki Tomita , Taku Ichiryu , Kiyoshi Suenaga
IPC分类号： F01D5/18 , F16D5/18
CPC分类号： F01D5/187 , F05D2240/81 , F05D2260/205 , F05D2260/2322
摘要： A gas turbine moving blade in which the moving blade operating in a high temperature operating gas is cooled from its interior by steam and the steam after being used for the cooling is recovered, by use of a simple structure. A supply side passage (10), through which steam (6) is supplied directly into a cooling passage (51) of a blade leading edge side (11), is provided within a blade root portion (2) and a pocket (19). One end of the pocket is connected to the supply side passage and the other end of which is connected to a cooling passage (52) of a blade trailing edge side (12). The pocket is covered with a plate, which extends in a blade chord direction on an outer peripheral side face of the blade root portion between a blade platform and a rotor plate. Thus, efficiency of the gas turbine can be effectively enhanced.
摘要翻译：一种燃气轮机动叶片，其中在高温操作气体中操作的移动叶片由其内部由蒸汽冷却，并且在用于冷却之后蒸汽被回收，通过使用简单的结构。供给侧通道（10）设置在叶片根部（2）和袋（19）内，蒸汽（6）直接供给到叶片前缘侧（11）的冷却通道（51）。袋的一端连接到供给侧通道，另一端连接到叶片后缘侧（12）的冷却通道（52）。该口袋被覆盖有板，其在刀片平台和转子板之间的叶片根部的外周侧面上以叶片弦方向延伸。因此，能够有效地提高燃气轮机的效率。

22. 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。

23. 发明授权

US6077034A Blade cooling air supplying system of gas turbine 失效
标题翻译：燃气轮机叶片冷却空气供应系统
公开(公告)号：US6077034A
公开(公告)日：2000-06-20
申请号：US38451
申请日：1998-03-11
申请人： Yasuoki Tomita , Hiroki Fukuno , Yukihiro Hashimoto , Kiyoshi Suenaga
发明人： Yasuoki Tomita , Hiroki Fukuno , Yukihiro Hashimoto , Kiyoshi Suenaga
IPC分类号： F01D5/08 , F01D5/18 , F01D9/02 , F01D9/04 , F01D9/06 , F01D11/04 , F02C7/18
CPC分类号： F01D5/08 , F01D5/187 , F01D9/065 , F05D2260/2212
摘要： In the present disclosure, an air pipe extends through a stationary blade between outer and inner shrouds. Further, an air passage is directed to a lower portion of the stationary blade and is communicated with the air pipe so that a serpentine cooling passage is formed. The air enters a cavity from the air passage and is discharged to a gas passage through an air hole, a passage and a seal. Thus, the cavity is sealed at a high pressure. Cooling air is supplied from the air passage to a rotating blade through a cooling air hole, a cooling air chamber, a radial hole and a lower portion of a platform. The stationary blade is cooled by the air through the air passage. The cooling air can be supplied to the rotating blade at a low temperature and a high pressure as they are. Accordingly, the air can be also supplied to the rotating blade when a rotor is cooled by vapor.
摘要翻译：在本公开中，空气管在外护罩和内护罩之间延伸穿过固定刀片。此外，空气通道被引导到固定叶片的下部并且与空气管连通，从而形成蛇形冷却通道。空气从空气通道进入空腔，并通过气孔，通道和密封件排放到气体通道。因此，空腔在高压下被密封。冷却空气从空气通道通过冷却空气孔，冷却空气室，径向孔和平台的下部供应到旋转叶片。固定叶片由空气通过空气通道冷却。冷却空气可以以低温和高压直接供给到旋转叶片。因此，当转子被蒸汽冷却时，空气也可以供应到旋转叶片。

24. 发明授权

US6036440A Gas turbine cooled moving blade 失效
标题翻译：燃气轮机冷却动叶片
公开(公告)号：US6036440A
公开(公告)日：2000-03-14
申请号：US53559
申请日：1998-04-01
申请人： Yasuoki Tomita , Hiroki Fukuno , Kiyoshi Suenaga
发明人： Yasuoki Tomita , Hiroki Fukuno , Kiyoshi Suenaga
IPC分类号： F01D5/18 , F02C7/18 , F01D5/08
CPC分类号： F01D5/187 , B22C21/14 , F05D2260/22141 , F05D2260/2322
摘要： The present invention relates to a gas turbine cooled moving blade in order to cool the gas turbine using steam alone. In the moving blade, two cavities are installed in the lower part of the moving blade root section of the moving blade, a steam inlet is located in one cavity, and a steam outlet is installed in the other cavity. Steam is charged from the steam inlet and passes through a serpentine cooling passage consisting of a plurality of steam passages, and discharged to the steam outlet and collected. Bypasses are located near the base of the moving blade in the middle of each steam passage, so that cold steam on the leading edge side can be led into the bypass, mixed with the hot steam which comes from the tip section side and goes into the next downstream section of the steam passage, and flows to an upstream portion of the steam passage, thereby equalizing the steam temperature and cooling the steam over the entire range from the upstream to downstream of the steam flow. A turbulator is installed in the middle of steam passage in order to generate turbulence and enhance heat transfer. Since the moving blade is evenly cooled by steam alone without using air, and the steam is then collected, the performance of the gas turbine can be enhanced.
摘要翻译：本发明涉及一种燃气轮机冷却的动叶片，以便仅使用蒸汽冷却燃气轮机。在移动叶片中，两个空腔安装在动叶片的动叶片根部的下部，蒸汽入口位于一个空腔中，蒸汽出口安装在另一腔中。蒸汽从蒸汽入口充入，并通过由多个蒸汽通道组成的蛇形冷却通道，并排放到蒸汽出口并收集。旁路位于每个蒸汽通道中间的移动叶片的基部附近，使得前缘侧的冷蒸汽可以被引导到旁路中，与来自尖端部分侧的热蒸汽混合并进入蒸汽通道的下游下游部分，并且流到蒸汽通道的上游部分，从而在蒸汽流的上游到下游的整个范围内均衡蒸汽温度并冷却蒸汽。湍流器安装在蒸汽通道的中部，以产生湍流并增强热传递。由于移动叶片在不使用空气的情况下均匀地被蒸汽均匀地冷却，所以随后收集蒸汽，可以提高燃气轮机的性能。

25. 发明授权

US06036436A Gas turbine cooling stationary vane 有权
标题翻译：燃气轮机冷却静止叶片
公开(公告)号：US06036436A
公开(公告)日：2000-03-14
申请号：US155787
申请日：1998-10-02
申请人： Hiroki Fukuno , Yasuoki Tomita , Kiyoshi Suenaga
发明人： Hiroki Fukuno , Yasuoki Tomita , Kiyoshi Suenaga
IPC分类号： F01D5/20 , F01D5/18 , F01D9/02 , F02C7/18
CPC分类号： F01D5/187 , F05D2240/81 , F05D2260/201 , F05D2260/202 , F05D2260/2212 , F05D2260/2322
摘要： There is provided a cooled stationary blade of a gas turbine in which the portions which can be cooled sufficiently by air are air-cooled, and the portions which are difficult to cool by air are steam-cooled, by which high temperatures can be overcome. In a stationary blade 1, there is formed a serpentine passage 3 in which cooling steam flows and an air passage 10 adjacent to the trailing edge portion and separated from the serpentine passage 3. Also, an outside shroud 4 is formed with an air cooling passage 16 at the outer edge portion and a steam impingement cooling portion 17 and an air impingement cooling portion 18 on the inside of the air cooling passage 16. An inside shroud 11 is provided with an air cooling passage 19 at the outer edge portion and shaped holes 20 formed on the inside of the air cooling passage 19. The air flowing out through the shaped holes 20 performs film cooling.
摘要翻译： PCT No.PCT / JP98 / 00206 Sec。 371日期：1998年10月2日 102（e）1998年10月2日日期PCT提交1998年1月21日PCT公布。公开号WO98 / 34013 日本1998年8月6日提供了一种燃气轮机的冷却固定叶片，其中可由空气充分冷却的部分被空气冷却，并且由空气难以冷却的部分被蒸汽冷却，由此高温度可以克服。在固定叶片1中，形成有冷却蒸汽流过的蛇形通道3和与后缘部分相邻并与蛇形通道3分离的空气通道10.另外，外部护罩4形成有空气冷却通道 16和外侧边缘部分的蒸汽冲击冷却部分17和空气冷却通道16内部的空气冲击冷却部分18.内部护罩11在外边缘部分设有空气冷却通道19， 20形成在空气冷却通道19的内部。通过成形孔20流出的空气进行膜冷却。

26. 发明授权

US5980202A Gas turbine stationary blade 失效
标题翻译：燃气轮机固定叶片
公开(公告)号：US5980202A
公开(公告)日：1999-11-09
申请号：US35587
申请日：1998-03-05
申请人： Yasuoki Tomita , Kiyoshi Suenaga , Taku Ichiryu
发明人： Yasuoki Tomita , Kiyoshi Suenaga , Taku Ichiryu
IPC分类号： F01D5/18 , F01D9/06 , F01D11/02 , F01D11/04
CPC分类号： F01D11/04 , F01D11/02 , F01D5/187 , F01D9/065 , F05D2240/81
摘要： A gas turbine stationary blade having a cooling medium passage and outer and inner shrouds in a blade section, comprising a hollow portion in the blade section, the hollow portion including a plurality of chambers divided in the chord direction, the cooling medium passage being formed by connecting the divided chambers in series, one of the chambers located in the center with respect to the chord direction being formed as a sealing air passage in order to allow a cooling medium to flow from the outside of the outer shroud to the bore of the inner shroud.
摘要翻译：一种燃气轮机固定叶片，其具有冷却介质通道和叶片部分中的外护罩和外护罩，包括叶片部分中的中空部分，所述中空部分包括沿弦弦方向分开的多个室，所述冷却介质通道由连接分开的室，其中一个相对于弦方向位于中心的腔室形成为密封空气通道，以便使冷却介质从外护罩的外部流动到内罩的孔裹尸布。

27. 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。

28. 发明授权

US06254346B1 Gas turbine cooling moving blade 失效
标题翻译：燃气轮机冷却动叶片
公开(公告)号：US06254346B1
公开(公告)日：2001-07-03
申请号：US09046865
申请日：1998-03-24
申请人： Hiroki Fukuno , Yasuoki Tomita , Kiyoshi Suenaga
发明人： Hiroki Fukuno , Yasuoki Tomita , Kiyoshi Suenaga
IPC分类号： F01D518
CPC分类号： F01D5/187 , F05D2240/81 , F05D2260/2212
摘要： The present invention relates to a gas turbine cooling moving blade and is applied to a large-sized blade for a high temperature so as to reduce its thickness and increase cooling efficiency and easily process the moving blade. A cavity is formed in the interior of the moving blade from the root portion to a shroud at the tip of the moving blade. Many turbulators are arranged in parallel with each other on an inner wall face of the moving blade. Cooling air from a turbine rotor enters the cavity formed within the moving blade from a cooling air inlet. This cooling air is dispersed and disturbed by the turbulators so that heat transfer is improved. Accordingly, the moving blade is efficiently cooled by the cooling air in comparison with a conventional cooling system having a multiplicity of holes. The cooling air is then discharged out of a cooling air outlet through air cooling holes of the shroud located at the tip of the moving blade. Accordingly, the proportion of the hollow space within the moving blade is increased by the cavity and the moving blade is made light in weight. The moving blade is more easily processed and the cooling efficiency of the moving blade is increased.
摘要翻译：本发明涉及一种燃气轮机冷却运动叶片，并被应用于高温度的大型叶片，以便减小其厚度并提高冷却效率并容易地处理动叶片。在动叶片的内部形成有从根部到动叶片顶端处的护罩的空腔。许多湍流器在动叶片的内壁面上彼此平行地排列。来自涡轮转子的冷却空气从冷却空气入口进入形成在活动叶片内的空腔。这种冷却空气被紊流器分散和干扰，从而改善了传热。因此，与具有多个孔的常规冷却系统相比，移动叶片被冷却空气有效地冷却。然后，冷却空气通过位于动叶片顶端的护罩的空气冷却孔从冷却空气出口排出。因此，通过空腔使活动叶片内的中空空间的比例增加，使动叶片重量轻。动叶片更容易加工，动叶片的冷却效率提高。

29. 发明授权

US06253537B1 Revolution speed control method in gas turbine shutdown process 有权
标题翻译：燃气轮机关机过程中的转速调速方法
公开(公告)号：US06253537B1
公开(公告)日：2001-07-03
申请号：US09380460
申请日：1999-09-03
申请人： Kiyoshi Suenaga , Yukihiro Hashimoto , Yasuoki Tomita
发明人： Kiyoshi Suenaga , Yukihiro Hashimoto , Yasuoki Tomita
IPC分类号： F02C700
CPC分类号： F02C9/46 , F01D21/06 , F05D2270/02 , F05D2270/091 , F05D2270/112
摘要： Stress occurring in a moving blade in a gas turbine stopping process is decreased. Time t1 is load decrease start or fuel throttling start, time t2 is no load operation start, time t3 is fuel shut-off and time t4 is a time of largest stress. A 4/4 load maintained until t1 decreases gradually to a 0/4 load at t2, which is then maintained until t3 and then decreases further. The rotational speed is the rated speed until t2, at which point it is controlled to be decreased gradually to about 60% of the rated rotational speed at t3. The metal differential temperature between a moving blade point A and a platform point B is constant until t1 and is then decreased slightly between t1 and t2 and between t2 and t3. Differential temperature &Dgr;t, largest after t3, occurs at t4. Stress occurring in the moving blade, while decreasing between t1 and t3, becomes largest at t4 by the effect of centrifugal force and thermal stress, but as the rotational speed is decreased to about 60% of the rated rotational speed at t3 and the metal temperature is also decreased as compared with the prior art, the influence of the centrifugal force and the differential temperature is decreased, whereby stress occurring in the moving blade is mitigated.
摘要翻译：在燃气轮机停止过程中在动叶片中产生的应力减小。时间t1是负载下降开始或燃料节流启动，时间t2是空载运行开始，时间t3是燃料切断，时间t4是最大应力的时间。一直保持4秒的负载，直到t1在t2时逐渐减小到0/4负载，然后保持到t3，然后进一步减小。转速为直到t2为止的额定转速，此时控制为逐渐减小到t3时的额定转速的约60％。动叶片点A和平台点B之间的金属温差恒定直到t1，然后在t1和t2之间以及在t2和t3之间略微减小。差分温度DELTAt，t3之后最大，出现在t4。在t1和t3之间减小的动作叶片的应力通过离心力和热应力的影响在t4处变得最大，但是随着转速降低到t3的额定转速的大约60％，金属温度与现有技术相比也降低，离心力和温差的影响减小，从而减轻了动叶片中的应力。

30. 发明授权

US6039531A Gas turbine blade 失效
标题翻译：燃气轮机叶片
公开(公告)号：US6039531A
公开(公告)日：2000-03-21
申请号：US34130
申请日：1998-03-03
申请人： Kiyoshi Suenaga , Yasuoki Tomita , Hiroki Fukuno
发明人： Kiyoshi Suenaga , Yasuoki Tomita , Hiroki Fukuno
IPC分类号： F01D5/18 , F01D5/20 , F01D5/30 , F01D11/08 , F02C7/16 , F02C7/18
CPC分类号： F01D5/20 , F01D5/186 , F01D5/3007
摘要： The present disclosure provides a gas turbine blade in which the tip end thereof is cooled effectively to decrease the metal temperature for the prevention of burning and the temperature gradient of blade metal is decreased to prevent the occurrence of cracking. In the gas turbine blade provided with a cooling passage therein, a protrusion is provided inwardly of the peripheral walls of the blade, which define the blade profile and the protrusion is positioned on the outer surface of blade tip end wall directly above a cooling passage within the blade.
摘要翻译：本公开提供一种燃气轮机叶片，其顶端被有效地冷却以降低金属温度以防止燃烧，并且降低叶片金属的温度梯度以防止发生裂纹。在其中设置有冷却通道的燃气轮机叶片中，突出部设置在叶片的周壁的内侧，其限定叶片轮廓，并且突起位于叶片末端壁的外侧表面上，直接位于冷却通道的正上方刀片。

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