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1. 发明授权

US06189891B1 Gas turbine seal apparatus 失效
标题翻译：燃气轮机密封装置
公开(公告)号：US06189891B1
公开(公告)日：2001-02-20
申请号：US09028664
申请日：1998-02-24
申请人： Yasuoki Tomita , Kazuharu Hirokawa , Hiroki Fukuno , Kiyoshi Suenaga , Yukihiro Hashimoto , Eisaku Ito
发明人： Yasuoki Tomita , Kazuharu Hirokawa , Hiroki Fukuno , Kiyoshi Suenaga , Yukihiro Hashimoto , Eisaku Ito
IPC分类号： F16J15447
CPC分类号： F01D11/02 , F01D11/001
摘要： A gas turbine seal structure provided between end portions of a moving blade platform and a stationary blade inside shroud. The sealing performance of the seal structure is improved by increasing the resistance to the flow of air. A seal plate (21, 31) is mounted to an end portion of a platform (2, 2′) of the moving blade (1) and a seal portion is formed by seal fins (22, 32) and a honeycomb seal (16, 17) disposed on a lower surface of an end portion (12a, 12b) of an inside shroud (12) of a stationary blade (11). Sealing air from the stationary blade (11) produces a high temperature in a cavity (14) and flows into a space (18, 19), and also air leaking from the cooling air of the moving blade (1) is able to escape into a high temperature combustion gas passage through a seal portion. However, since the seal plate has three seal fins (22, 32) that are inclined in a direction so as to oppose the air flow, air resistance is increased and the flow of air into the combustion gas passage is prevented.
摘要翻译：一种燃气轮机密封结构，其设置在活动叶片平台的端部和固定叶片内部的护罩内。通过增加对空气流动的阻力来改善密封结构的密封性能。密封板（21,31）安装在活动叶片（1）的平台（2,2'）的端部，密封部分由密封翅片（22,32）和蜂窝密封件（16）形成，17），其设置在固定叶片（11）的内侧护罩（12）的端部（12a，12b）的下表面上。来自固定叶片（11）的密封空气在空腔（14）中产生高温并流入空间（18,19），并且从活动叶片（1）的冷却空气泄漏的空气也能够逸出通过密封部分的高温燃烧气体通道。然而，由于密封板具有在与空气流相对的方向上倾斜的三个密封翅片（22,32），因此空气阻力增加，并且防止了进入燃烧气体通道的空气流。

2. 发明授权

US5967745A Gas turbine shroud and platform seal system 失效
标题翻译：燃气轮机罩和平台密封系统
公开(公告)号：US5967745A
公开(公告)日：1999-10-19
申请号：US28662
申请日：1998-02-24
申请人： Yasuoki Tomita , Hiroki Fukuno , Eisaku Ito , Kiyoshi Suenaga
发明人： Yasuoki Tomita , Hiroki Fukuno , Eisaku Ito , Kiyoshi Suenaga
IPC分类号： F01D5/02 , F01D9/04 , F01D11/00 , F01D11/04 , F01D11/12 , F02C7/18 , F02C7/28 , F01D11/02
CPC分类号： F01D11/001 , F01D11/127 , F02C7/28
摘要： A gas turbine shroud and platform seal system, which is constructed so that the flow of sealing air does not disturb a combustion gas flow, and thus any aerodynamic loss is reduced. The leaking air (60) leaks from between a platform (2) of moving blade (1) and an inside shroud (12) in a stationary blade (11). At a front or upstream side of the moving blade (1), the leaking air (60) flows along a S-shaped path within a space (8, 17) formed by a projecting end portion (12b) of the shroud, a honeycomb seal (14) and a projecting portion (4) of the platform. The air eventually flows out in the same flow direction as that of the combustion gas (50) along a surface of the platform (2). At a rear side of the moving blade (1), the leaking air (60) flows along an S-shaped path within a space (6, 9) formed by a projecting end portion (2b) of the platform, a projecting end portion (12b) of the shroud, a honeycomb seal (13) and a seal plate (3). The air eventually flows out in the same direction as that of the combustion gas (50) along a surface of the shroud (12). The air (60) flows in the same direction as the combustion gas (50), and thus a flow loss is reduced. Also, the air is not easily leaked, and a cooling effect of the platform and the shroud is increased due to a film cooling effect.
摘要翻译：一种燃气轮机罩和平台密封系统，其结构使得密封空气的流动不会干扰燃烧气体流动，因此减少了任何空气动力学损失。泄漏的空气（60）从静止叶片（11）的活动叶片（1）的平台（2）和内侧护罩（12）之间泄漏。在活动叶片（1）的前侧或上游侧，泄漏空气（60）沿着由护罩的突出端部（12b）形成的空间（8,17）内的S形路径流动，蜂窝密封件（14）和平台的突出部分（4）。空气最终沿着平台（2）的表面沿与燃烧气体（50）相同的流动方向流出。在活动叶片（1）的后侧，泄漏空气（60）沿着由平台的突出端部（2b）形成的空间（6,9）内的S形路径流动，突出端部（12b），蜂窝密封件（13）和密封板（3）。空气最终沿与护罩（12）的表面沿燃烧气体（50）相同的方向流出。空气（60）沿与燃烧气体（50）相同的方向流动，因此流动损失减少。此外，空气不容易泄漏，并且由于膜冷却效果，平台和护罩的冷却效果增加。

3. 发明授权

US6146098A Tip shroud for cooled blade of gas turbine 有权
标题翻译：燃气轮机冷却叶片的顶盖
公开(公告)号：US6146098A
公开(公告)日：2000-11-14
申请号：US242678
申请日：1999-02-22
申请人： Hiroki Fukuno , Yasuoki Tomita , Eisaku Ito
发明人： Hiroki Fukuno , Yasuoki Tomita , Eisaku Ito
IPC分类号： F01D5/08 , F01D5/18 , F01D5/20 , F01D5/22 , F01D11/10 , F02C7/18 , B63H1/14
CPC分类号： F01D11/10 , F01D5/18 , F01D5/187 , F01D5/225 , F05B2240/33 , F05D2240/81
摘要： A tip shroud for a moving blade that is made thin and light for use at a gas turbine downstream stage. Cooling air holes (13 to 16) having a slot shape, are formed in a tip shroud (11) of the moving blade (10). The cooling holes are opened in two side faces of the tip shroud to release the cooling air from the inside of the moving blade (10). In the upper face of the tip shroud 11, there are formed cooling air holes 20, which communicate with the higher pressure side in a combustion gas flow direction R to release the cooling air so that the cooling air flows from the higher pressure side to the lower pressure side so as to cool a high stress portion Y. A high stress portion X is likewise cooled with the cooling air coming from an adjoining moving blade. The slot shapes of the cooling air holes (13 to 16) allow the cooling air to flow widely, thereby cooling the face of the tip shroud (11), and the cooling air holes 20 cool the high stress portions X and Y effectively.
摘要翻译： PCT No.PCT / JP98 / 02689 Sec。一九九九年二月二十二日 102（e）1999年2月22日PCT PCT 1998年6月18日PCT公布。公开号WO98 / 59157 日期1998年12月30日用于在燃气轮机下游阶段使用的薄而轻的移动叶片的尖端罩。具有狭槽形状的冷却气孔（13至16）形成在活动叶片（10）的尖端罩（11）中。冷却孔在尖端护罩的两个侧面上打开，以从动叶片（10）的内部释放冷却空气。在顶部护罩11的上表面形成有冷却空气孔20，其在燃烧气体流动方向R上与高压侧连通以释放冷却空气，使得冷却空气从高压侧流向低压侧，以冷却高应力部分Y.同样，高应力部分X同样地冷却来自邻接的活动叶片的冷却空气。冷却空气孔（13〜16）的槽形状允许冷却空气大量流动，从而冷却尖端罩（11）的表面，并且冷却空气孔20有效地冷却高应力部分X和Y.

4. 发明授权

US06196798B1 Gas turbine cooling blade 有权
标题翻译：燃气轮机冷却叶片
公开(公告)号：US06196798B1
公开(公告)日：2001-03-06
申请号：US09242330
申请日：1999-02-11
申请人： Hiroki Fukuno , Yasuoki Tomita , Shigeyuki Maeda , Yukihiro Hashimoto , Kiyoshi Suenaga
发明人： Hiroki Fukuno , Yasuoki Tomita , Shigeyuki Maeda , Yukihiro Hashimoto , Kiyoshi Suenaga
IPC分类号： F01D518
CPC分类号： F01D5/186 , F01D5/18
摘要： A number of air-transpiration holes (4) are provided at a leading edge portion (2) of a cooled blade (1). Cooling air flowing through a cooling air passage (15) formed inside of the blade blows out to the blade surface of the leading edge portion (2) of the cooled blade (1) by way of the air-transpiration holes (4), to thereby shower-head cool the surface of the leading edge portion (2). The air-transpiration holes (4) are formed so as to extend substantially orthogonal to the leading edge surface of the cooled blade (1) such that the acute-angled portions are eliminated, whereby thermal stress is reduced and cracking is prevented.
摘要翻译：在冷却叶片（1）的前缘部分（2）处设置有多个空气蒸发孔（4）。流过形成在叶片内的冷却风道（15）的冷却空气通过空气蒸发孔（4）吹向冷却叶片（1）的前缘部（2）的叶片表面，至从而喷淋头对前缘部分（2）的表面进行冷却。空气蒸发孔（4）形成为基本上垂直于冷却叶片（1）的前缘表面延伸，使得锐角部分被消除，从而减少热应力并防止开裂。

5. 发明授权

US06196791B1 Gas turbine cooling moving blades 有权
标题翻译：燃气轮机冷却动叶片
公开(公告)号：US06196791B1
公开(公告)日：2001-03-06
申请号：US09202951
申请日：1998-12-23
申请人： Yasuoki Tomita , Hiroki Fukuno , Sunao Aoki , Kiyoshi Suenaga
发明人： Yasuoki Tomita , Hiroki Fukuno , Sunao Aoki , Kiyoshi Suenaga
IPC分类号： F01D518
CPC分类号： F02C7/12 , F01D5/081 , F01D5/18
摘要： In gas turbine cooled moving blade, a cooling air passage is made shortest and temperature elevation and pressure drop of the cooling air are suppressed. The cooling air passage (16) is bored in a turbine cylinder wall (15) located below a first stage stationary blade (11). The cooling air passage (16) communicates at one end (16a) with a turbine cylinder and at the other end (16b) with a space (13) between the stationary blade and the moving blade. The passage (16) is directed to an air inflow hole (6) provided in a shank portion (4) of a lower portion of a platform (2) of the moving blade (1). Cooling air is jetted from the cooling air passage (16) toward the air inflow hole (6) so as to flow into the shank portion (4) and then into the moving blade (1) for cooling thereof. An axis (17) of the cooling air passage (16) is directed so as to deviate in a rotational circumferential direction by an angle determined by the velocity of the cooling air jetted from the cooling air passage (16) and the rotational velocity of the moving blade (1) from position of the air inflow hole when the moving blade (1) stands still in row with the stationary blade (11) in rotor axial direction. Thus, the cooling air can be jetted in an optimal direction with the shortest distance, and the temperature elevation and pressure drop of the cooling air can be suppressed to minimum.
摘要翻译：在燃气轮机冷却动叶片中，冷却空气通道最短，并且冷却空气的温度升高和压降被抑制。冷却空气通道（16）在位于第一级固定叶片（11）下方的涡轮机气缸壁（15）中钻孔。冷却空气通道（16）在一端（16a）与涡轮机气缸连通，另一端（16b）在固定叶片和动叶片之间具有空间（13）。通道（16）被引导到设置在活动叶片（1）的平台（2）的下部的柄部分（4）中的空气流入孔（6）。冷却空气从冷却空气通路（16）向空气流入孔（6）喷射，从而流入柄部（4），然后进入动叶片（1）进行冷却。冷却空气通路16的轴线（17）被引导为以从冷却空气通路（16）喷射的冷却空气的速度和旋转速度确定的旋转圆周方向偏离角度当动叶片（1）在转子轴向与静叶片（11）静置时，从动空气流入孔的位置移动叶片（1）。因此，可以以最短的距离沿最佳方向喷射冷却空气，并且可以将冷却空气的温度升高和压降降低到最小。

6. 发明授权

US6142730A Gas turbine cooling stationary blade 有权
标题翻译：燃气轮机冷却固定叶片
公开(公告)号：US6142730A
公开(公告)日：2000-11-07
申请号：US202690
申请日：1998-12-21
申请人： Yasuoki Tomita , Kenichi Arase , Hiroki Fukuno , Hideki Murata , Kiyoshi Suenaga , Tsuyoshi Kitamura
发明人： Yasuoki Tomita , Kenichi Arase , Hiroki Fukuno , Hideki Murata , Kiyoshi Suenaga , Tsuyoshi Kitamura
IPC分类号： F01D9/02 , F01D5/18 , F01D9/04 , F01D9/06 , F02C7/18
CPC分类号： F01D9/065 , F01D5/187 , F05D2240/81 , Y02T50/676
摘要： In a cooled gas turbine stationary blade, both steam cooling and air cooling are utilized to reduce the amount of cooling air. In the stationary blade having outer and inner shrouds 1, 21 and steam passages 10A, 10B, 10C, 10D and 10E which are communicated with each other and in which a sealing air feed tube 2 passes through a central portion thereof, steam covers 3, 4 are provided in the outer shroud 1, and steam S is introduced from a steam feed port 5. The steam S passes through serpentine passages 10A to 10E and is recovered from the steam outlet 12 after cooling the central portion of the outer shroud 1 by means of an impingement plate 8. A portion of the steam of the passage 10A is introduced from the impingement plate 25 to a steam sump 24 to cool the central portion of the inner shroud 21 and pass through the passage 10D to be recovered from the steam outlet port 12. On the other hand, cooling air is fed from cooling air feed ports 6 and 26 to peripheral portions of the outer and inner shrouds 1, 21, and is discharged to the outside from the rear sides thereof, respectively, and the cooling air is further fed from a cooling air feeding port 7 to the passage 10E on the rear edge of the blade to cool the rear edge of the blade. Only the narrow portions where it is difficult for the steam to pass are air-cooled to thereby reduce the amount of the cooling air.
摘要翻译： PCT No.PCT / JP98 / 01959 Sec。 371 1998年12月21日第 102（e）日期1998年12月21日PCT提交1998年4月28日PCT公布。公开号WO98 / 50685 PCT 日期1998年11月12日在冷却式燃气轮机固定叶片中，蒸汽冷却和空气冷却都用于减少冷却空气的量。在具有彼此连通并且密封空气供给管2穿过其中心部分的外护罩1和21以及蒸汽通道10A，10B，10C，10D和10E的固定刀片中，蒸汽罩3， 4设置在外护罩1中，并且蒸汽S从蒸汽供给口5引入。蒸汽S通过蛇形通道10A至10E，并且在冷却外护罩1的中心部分之后从蒸汽出口12回收，冲击板8的装置。通道10A的蒸汽的一部分从冲击板25引入蒸汽槽24，以冷却内护罩21的中心部分，并通过通道10D以从蒸汽中回收另一方面，冷却空气从冷却空气供给口6和26被供给到外护罩1和外护罩21的周边部分，并且分别从其后侧排出到外部，冷却空气很冷她从冷却空气供给口7进入叶片后缘的通道10E，以冷却叶片的后边缘。只有蒸汽难以通过的狭窄部分被空气冷却，从而减少冷却空气的量。

7. 发明授权

US6089826A Turbulator for gas turbine cooling blades 有权
标题翻译：燃气轮机冷却叶片的涡轮机
公开(公告)号：US6089826A
公开(公告)日：2000-07-18
申请号：US180469
申请日：1998-11-09
申请人： Yasuoki Tomita , Sunao Aoki , Hiroki Fukuno , Kiyoshi Suenaga
发明人： Yasuoki Tomita , Sunao Aoki , Hiroki Fukuno , Kiyoshi Suenaga
IPC分类号： F01D5/18 , F02C7/18
CPC分类号： F01D5/187 , F05D2260/2212 , F05D2260/22141
摘要： A gas turbine cooled blade has leading edge turbulators. A rounded tip portion of the leading edge portion cooling passage (3) is approximated by a triangular cooling passage (1) having orthogonal turbulators (11, 12) and a smoothly curved rear portion thereof of the leading edge portion cooling passage (3) is approximated by a square cooling passage 2 having oblique turbulators (13, 14).
摘要翻译： PCT No.PCT / JP98 / 01482 Sec。 371日期：1998年11月9日 102（e）1998年11月9日PCT PCT 1998年3月31日PCT公布。第WO98 / 44241号公报日期1998年10月8日燃气轮机冷却叶片具有前缘湍流器。前缘部分冷却通道（3）的圆形末端部分由具有正交湍流器（11,12）的三角形冷却通道（1）近似，其前缘部分冷却通道（3）的平滑弯曲的后部是由具有倾斜湍流器（13,14）的方形冷却通道2近似。

8. 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。

9. 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。

10. 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。

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