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.

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。

公开(公告)号：US6086329A

公开(公告)日：2000-07-11

申请号：US38070

申请日：1998-03-11

申请人： Yasuoki Tomita ,  Hiroki Fukuno ,  Eisaku Ito

发明人： Yasuoki Tomita ,  Hiroki Fukuno ,  Eisaku Ito

IPC分类号： F01D5/22 ,  F01D5/02 ,  F01D11/00 ,  F01D11/04 ,  F02C7/28

CPC分类号： F01D11/006

摘要： A seal plate at the platform portion of a gas turbine moving blade. The seal plate is inserted in a gap between the adjacent platforms at each end portion of a seal pin to prevent air from leaking to the outside. A groove is provided at each of four corners of the end portion of platform of the moving blade, and the seal plate is inserted to cover the gap so as to extend the end portions of the adjacent platforms, by which the gap between the platforms is blocked. A seal pin and end seal pins are inserted between the platforms to seal this portion. However, there is a gap at the end portions, so that cooling air leaks from the lower part of platform. Since the seal plate is inserted in the groove to block the gap, the sealing property is increased.

摘要翻译： 在燃气轮机动叶片的平台部分处的密封板。 密封板在密封销的每个端部处插入相邻平台之间的间隙中，以防止空气泄漏到外部。 在活动叶片的平台的端部的四个角部的每一个处设置有凹槽，并且插入密封板以覆盖间隙，以延伸相邻平台的端部，由此平台之间的间隙为 被阻止 密封销和端部密封销插入平台之间以密封该部分。 然而，在端部处存在间隙，使得冷却空气从平台的下部泄漏。 由于密封板插入凹槽以阻挡间隙，所以密封性能增加。

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。

公开(公告)号：US6132173A

公开(公告)日：2000-10-17

申请号：US42701

申请日：1998-03-17

申请人： Yasuoki Tomita ,  Hiroki Fukuno ,  Kenichi Arase ,  Toshiaki Sano

发明人： Yasuoki Tomita ,  Hiroki Fukuno ,  Kenichi Arase ,  Toshiaki Sano

IPC分类号： F01D5/08 ,  F01D5/18 ,  F01D5/30 ,  F02C3/30 ,  F02C7/18

CPC分类号： F01D5/187 ,  F05D2240/81 ,  F05D2260/2212 ,  F05D2260/2322

摘要： A cooled platform for a gas turbine moving blade which enables the platform to be cooled when the moving blade is cooled by steam. The moving blade is provided with a plurality of steam passages. Steam is introduced from the steam passage at the trailing edge portion, flows in a serpentine passage composed of other steam passages to cool the blade, and flows out to a blade root portion from a base portion of the steam passage at the leading edge portion, being recovered. Part of steam flowing into the platform from the base portion of the steam passage at the trailing edge portion enters first and second steam passages in the platform. On one side, the steam passes through first, third, and fourth steam passages, and on the other hand, the steam passes through second, fifth, and sixth steam passages. The steam is recovered together with the steam having cooled the blade at the base portion of steam passage at the leading edge portion. Therefore, the peripheral portion of a platform can be cooled by steam, air is not needed, and the platform can be cooled by steam when the steam cooling system is used to cool the blade.

摘要翻译： 一种用于燃气轮机移动叶片的冷却平台，其使得当移动叶片由蒸汽冷却时能够使平台冷却。 动叶片设有多个蒸汽通道。 蒸汽从后缘部分的蒸汽通道引入，在由其他蒸汽通道组成的蛇形通道中流动以冷却叶片，并从前缘部分的蒸汽通道的基部部分流出到叶片根部， 正在恢复。 在后缘部分从蒸汽通道的基部流入平台的蒸汽的一部分进入平台中的第一和第二蒸汽通道。 蒸汽一方面通过第一，第三和第四蒸汽通道，另一方面蒸汽通过第二，第五和第六蒸汽通道。 蒸汽与在前缘部分处的蒸汽通道的基部处将叶片冷却的蒸汽一起回收。 因此，平台的周边部分可以被蒸汽冷却，不需要空气，并且当蒸汽冷却系统用于冷却叶片时，平台可以被蒸汽冷却。

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。

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。

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。

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。

公开(公告)号：US6079944A

公开(公告)日：2000-06-27

申请号：US175990

申请日：1998-10-21

申请人： Yasuoki Tomita ,  Kenichi Arase ,  Naoki Hagi ,  Hiroki Fukuno

发明人： Yasuoki Tomita ,  Kenichi Arase ,  Naoki Hagi ,  Hiroki Fukuno

IPC分类号： F01D9/02 ,  F01D11/00 ,  F02C7/28 ,  F01D9/04

CPC分类号： F01D11/005 ,  F05D2240/10 ,  F05D2240/11

摘要： Seal plates for gas turbine stationary blade inner shrouds are made in a double cross type seal structure with a view to enhance sealing ability. Seal plates 1, 2 are mutually lapped and disposed in a turbine axial direction between inner shrouds 12 of stationary blades 11. End portion seal plate 5 is lapped on an end portion of the seal plate 2 and end portion seal plate 6 is lapped under an end portion of the seal plate 1. All these seal plates are fitted with their side end portions being inserted into groove 9a provided in the inner shrouds 12. Seal plates 3, 4 and seal plates 7, 8 engaged with the seal plates 3, 4 are also fitted between flange portions of the inner shrouds 12 with their side end portions being inserted into grooves 10a, 10b and grooves 9b, 9c, respectively. All the seal plates 1 to 8 are fitted between mutually opposing inner shrouds in turbine circumferential direction so as to cover cavity 24 between mutually adjacent shrouds, so that gaps between engaged portions of each seal plate and between the seal plates and seal ring support ring 13 are eliminated, thereby seal air 20 is prevented from leaking from the cavity 24.

摘要翻译： 用于燃气轮机固定叶片内护罩的密封板以双交叉密封结构制成，以提高密封能力。 密封板1,2在固定叶片11的内护罩12之间相互重叠配置在涡轮轴向。端部密封板5在密封板2的端部上搭接，并将端部密封板6在 所有这些密封板都装配有它们的侧端部插入到设置在内罩12中的槽9a中。密封板3,4和与密封板3,4接合的密封板7,8 也装配在内护罩12的凸缘部分之间，其侧端部分别插入槽10a，10b和槽9b，9c中。 所有的密封板1至8均安装在涡轮机周向上相互相对的内护罩之间，以便覆盖彼此相邻的护罩之间的空腔24，使得每个密封板的接合部分之间以及密封环和密封环之间的间隙支撑环13 被消除，从而防止密封空气20从空腔24泄漏。