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1. 发明授权

US5951250A Turbine cooling apparatus 失效
标题翻译：涡轮冷却装置
公开(公告)号：US5951250A
公开(公告)日：1999-09-14
申请号：US35616
申请日：1998-03-05
申请人： Kiyoshi Suenaga , Sunao Aoki , Yoshiaki Tsukuda , Youichi Iwasaki
发明人： Kiyoshi Suenaga , Sunao Aoki , Yoshiaki Tsukuda , Youichi Iwasaki
IPC分类号： F01D5/08 , F01D5/18 , F02C7/18 , B63H1/14
CPC分类号： F01D5/085 , F01D5/081
摘要： A turbine cooling apparatus comprising a turbine disk having a plurality of moving blades, a torque tube coupled coaxially to one surface side of the turbine disk and having a thick stepped inner wall portion in the central portion thereof, an air separator fitted on the torque tube with the inner surface thereof in contact with the outer surface of the torque tube so that a passage through which cooling air is supplied to the moving blades via the turbine disk is defined between the air separator and the torque tube, and a torque tube cooling hollow portion provided along and in the vicinity of the outer surface of the thick stepped wall portion of the torque tube.
摘要翻译：一种涡轮机冷却装置，包括具有多个活动叶片的涡轮盘，与所述涡轮盘的一个表面侧同轴配置的扭矩管，并且在其中心部分具有厚的阶梯状内壁部分，安装在所述扭矩管上的空气分离器其内表面与扭矩管的外表面接触，从而在空气分离器和扭矩管之间限定了通过涡轮盘将冷却空气供应到活动叶片的通道，以及扭矩管冷却空心管在转矩管的厚阶梯状壁部的外表面附近设置的部分。

2. 发明授权

US06217279B1 Device for sealing gas turbine stator blades 有权
标题翻译：燃气轮机定子叶片密封装置
公开(公告)号：US06217279B1
公开(公告)日：2001-04-17
申请号：US09230820
申请日：1999-02-10
申请人： Toshishige Ai , Masanori Yuri , Yasuoki Tomita , Kiyoshi Suenaga , Sunao Aoki , Hiroki Fukuno
发明人： Toshishige Ai , Masanori Yuri , Yasuoki Tomita , Kiyoshi Suenaga , Sunao Aoki , Hiroki Fukuno
IPC分类号： F01D518
CPC分类号： F01D9/065 , F01D11/001 , F02C7/18
摘要： A sealing device for a gas turbine stator blade, in which an outer shroud (32) is mounted by heat insulating rings (32a,32b) on a blade ring (50). The blade ring (50) has a first air hole (1), which communicates with a space (53), and a second air hole (51), which communicates with a seal tube (2). The seal tube (2) is inserted into the second air hole (51), and a spring (6) is arranged between a projection (4) of the tube (2) and a retaining portion (5) of the air hole (51) to removably secure the seal tube (2). Cooling air (54) flows through the first air hole (1) to cool the shrouds and the inside of a stator blade (31) until it is released from the trailing edge of the blade. The cooling air also flows into a cavity (36) so that a high pressure can be maintained without a pressure loss because the tube (2) is independent of the space (53) in the blade ring.
摘要翻译：一种用于燃气轮机定子叶片的密封装置，其中外护罩（32）通过隔离环（32a，32b）安装在叶片环（50）上。叶片环（50）具有与空间（53）连通的第一空气孔（1）和与密封管（2）连通的第二空气孔（51）。密封管（2）插入到第二空气孔（51）中，弹簧（6）布置在管（2）的突出部（4）和气孔（51）的保持部分（5）之间）以可拆卸地固定密封管（2）。冷却空气（54）流过第一空气孔（1）以冷却护罩和定子叶片（31）的内部，直到其从叶片的后缘释放。冷却空气也流入空腔（36），从而由于管（2）独立于叶片环中的空间（53）而能够保持高压而没有压力损失。

3. 发明授权

US5971707A Gas turbine moving blade steam cooling system 失效
标题翻译：燃气轮机动叶片蒸汽冷却系统
公开(公告)号：US5971707A
公开(公告)日：1999-10-26
申请号：US109379
申请日：1998-07-02
申请人： Kazuo Uematsu , Rintaro Chikami , Yasuoki Tomita , Hiroki Fukuno , Sunao Aoki , Toshiaki Sano , Yukihiro Hashimoto , Kiyoshi Suenaga , Kazuharu Hirokawa
发明人： Kazuo Uematsu , Rintaro Chikami , Yasuoki Tomita , Hiroki Fukuno , Sunao Aoki , Toshiaki Sano , Yukihiro Hashimoto , Kiyoshi Suenaga , Kazuharu Hirokawa
IPC分类号： F01D5/18 , F01D11/00 , B65H1/14 , F01D5/08
CPC分类号： F01D5/18 , F01D11/006 , F05D2260/2322
摘要： A gas turbine moving blade steam cooling system in which leakage of steam for cooling a moving blade is prevented and thermal stress at a blade root end portion is mitigated. Each end portion of a blade root portion (3) of the moving blade (1) is projected so as to form a projection portions (4a, 4b). A steam passage 5 is provided between the projection portions (4a, 4b) and a steam supply port 5a and a steam recovery port (5b) are provided downwardly with the respect to the steam passage 5. The steam supply port (5a) connects to a steam supply passage (20) and the steam recovery port (5b) connects to a steam recovery passage (21). Steam is supplied from the steam supply port (5a) into a blade interior and is recovered through the steam recovery port (5b). Side surface seal plates (6, 7 and 8) are provided for preventing steam leakage. The steam cools the moving blade (1) and can be recovered without leakage and stress concentration due to heat at the projection portions (4a, 4b) of the blade root end portion.
摘要翻译：一种燃气轮机动叶片蒸汽冷却系统，其中防止用于冷却动叶片的蒸汽泄漏并减轻叶片根部端部处的热应力。活动叶片（1）的叶片根部（3）的每个端部突出以形成突出部分（4a，4b）。蒸汽通道5设置在突出部分（4a，4b）和蒸汽供应口5a之间，蒸汽回收口（5b）相对于蒸汽通道5向下设置。蒸汽供应口（5a）连接到蒸汽供应通道（20）和蒸汽回收口（5b）连接到蒸汽回收通道（21）。蒸汽从蒸汽供给口（5a）供给到叶片内部，并通过蒸汽回收口（5b）回收。侧面密封板（6,7和8）用于防止蒸汽泄漏。蒸汽冷却活动叶片（1），并且可以在叶片根部的突出部分（4a，4b）处由于热量而没有泄漏和应力集中而恢复。

4. 发明授权

US06481967B2 Gas turbine moving blade 有权
标题翻译：燃气轮机动叶片
公开(公告)号：US06481967B2
公开(公告)日：2002-11-19
申请号：US09790975
申请日：2001-02-23
申请人： Yasuoki Tomita , Yukihiro Hashimoto , Kiyoshi Suenaga , Hisato Arimura , Shunsuke Torii , Jun Kubota , Akihiko Shirota , Sunao Aoki , Tatsuo Ishiguro
发明人： Yasuoki Tomita , Yukihiro Hashimoto , Kiyoshi Suenaga , Hisato Arimura , Shunsuke Torii , Jun Kubota , Akihiko Shirota , Sunao Aoki , Tatsuo Ishiguro
IPC分类号： F01D518
CPC分类号： F01D5/20 , F01D5/186 , F01D5/187 , F05D2240/81 , F05D2250/185 , F05D2260/22141
摘要： A gas turbine moving blade is provided which prevents occurrence of cracks caused by thermal stresses due to temperature differences between a blade and a platform while the gas turbine is being stopped. During steady operation time of the moving blade, cooling air enters cooling passages to flow through other cooling passages for cooling the blade, and then to flow out of the blade. A recessed portion having a smooth curved surface is provided in the platform near a blade fitting portion on the blade trailing edge side. A fillet of the blade fitting portion on the blade trailing edge side has a curved surface with curvature larger than that of a conventional blade fitting portion. A hub slot below the fillet, for blowing air, has a cross sectional area larger than other slots of the blade trailing edge. A thermal barrier coating is applied to the blade surface. By the above construction, thermal stresses due to temperature differences between the blade and the platform during gas turbine stoppage are made smaller and occurrence of cracks is prevented.
摘要翻译：提供了一种燃气轮机动叶片，其防止在燃气轮机停止时由于叶片和平台之间的温度差引起的热应力的发生。在运动叶片的稳定运行时间内，冷却空气进入冷却通道，流过其它冷却通道，以冷却叶片，然后流出叶片。具有光滑曲面的凹部在叶片后缘侧的叶片嵌合部附近设置在平台上。叶片后缘侧的叶片嵌合部的圆角具有比现有的叶片嵌合部曲率大的曲率的曲面。在圆角下方的用于吹送空气的轮毂槽的横截面积大于叶片后缘的其它槽。将热障涂层施加到叶片表面。通过上述结构，使得在燃气轮机停止期间由于叶片和平台之间的温度差导致的热应力变小，并且防止了裂纹的发生。

5. 发明授权

US06257830B1 Gas turbine blade 有权
标题翻译：燃气轮机叶片
公开(公告)号：US06257830B1
公开(公告)日：2001-07-10
申请号：US09230983
申请日：1999-06-02
申请人： Masaaki Matsuura , Kiyoshi Suenaga , Sunao Aoki , Kazuo Uematsu , Hiroki Fukuno , Yasuoki Tomita
发明人： Masaaki Matsuura , Kiyoshi Suenaga , Sunao Aoki , Kazuo Uematsu , Hiroki Fukuno , Yasuoki Tomita
IPC分类号： F01D518
CPC分类号： F01D5/147 , F01D5/187 , F05D2260/2322
摘要： In a steam cooling system proposed heretofore, high-pressure steam is supplied into an internal space of a blade for effecting cooling thereof with the high-pressure steam to thereby recover heat energy. This system however suffers from problems concerning the strength of the blade and the like. The present invention solves these problems and provides a gas-turbine blade which does not suffer from problems concerning the strength thereof nor problems concerning the flow of high-pressure steam. To this end, a coolant flow passage is formed within the blade extending in the longitudinal direction of the blade, and reinforcing ribs which interconnects a dorsal wall and a ventral wall of the blade is disposed within the coolant flow passage so as to extend in the flow direction of the coolant. Hence, the strength of the blade can be ensured without any obstacle to the flow of the coolant.
摘要翻译：在迄今为止提出的蒸汽冷却系统中，将高压蒸汽供应到叶片的内部空间中，以利用高压蒸汽冷却，从而回收热能。然而，该系统存在关于叶片等的强度的问题。本发明解决了这些问题，提供了一种不存在与强度相关的问题的燃气轮机叶片，也不会涉及高压蒸汽的流动问题。为此，在刀片的纵向延伸的叶片内形成冷却剂流动通道，并且将与叶片的背壁和腹壁相互连接的加强筋设置在冷却剂流动通道内，以便在冷却液的流动方向。因此，可以确保叶片的强度，而不会妨碍冷却剂的流动。

6. 发明授权

US6079946A Gas turbine blade 失效
标题翻译：燃气轮机叶片
公开(公告)号：US6079946A
公开(公告)日：2000-06-27
申请号：US44746
申请日：1998-03-19
申请人： Kiyoshi Suenaga , Sunao Aoki , Kazuo Uematsu
发明人： Kiyoshi Suenaga , Sunao Aoki , Kazuo Uematsu
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F05D2240/81 , F05D2260/2322
摘要： In the cooling system for the gas turbine blade, the apparatus of the present disclosure ensures cooling of the trailing edge part of the blade for which machining is difficult, while aiming at improvement of the thermal efficiency. The steam cooling structure for carrying out heat recovery-type steam cooling is employed to the leading edge part and the central part of the blade where machining is easy because of its large thickness, and the convection cooling end film cooling are employed for the trailing edge part of the blade where the thickness is small, using steam cooling and air cooling at the same time.
摘要翻译：在用于燃气轮机叶片的冷却系统中，本公开的装置确保了难以加工的叶片的后缘部分的冷却，同时旨在提高热效率。用于进行热回收式蒸汽冷却的蒸汽冷却结构用于叶片的前缘部分和中心部分，其中由于其厚度大而容易加工，并且对流冷却端膜冷却用于后缘厚度较小的叶片部分，同时使用蒸汽冷却和空气冷却。

7. 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。

8. 发明授权

US6151881A Air separator for gas turbines 有权
标题翻译：燃气轮机气分离器
公开(公告)号：US6151881A
公开(公告)日：2000-11-28
申请号：US242293
申请日：1999-02-11
申请人： Toshishige Ai , Yoichi Iwasaki , Sunao Aoki , Yukihiro Hashimoto , Kiyoshi Suenaga
发明人： Toshishige Ai , Yoichi Iwasaki , Sunao Aoki , Yukihiro Hashimoto , Kiyoshi Suenaga
IPC分类号： F01D5/08 , F01D11/02 , B63H1/14
CPC分类号： F01D11/02 , F01D5/081 , F01D5/085
摘要： An air separator for a gas turbine, in which cracks are prevented from occurring at a flange portion of the air separator due to fretting fatigue. The air separator (20) has a cylindrical split structure formed by two separator members (20-1 and 20-2), of which one of the separators (20-1) is mounted on a rotor (1) whereas the other separator member (20-2) is mounted on a disc portion (7) on a side of a moving blade (2) by bolts (28) extending through bolt holes (23) formed in a flange portion (22). Cooling air from a compressor enters a space (6) from a duct (5) and passes to a passage (32) from a clearance (33) so that it is fed to air feed holes (43) and radial holes (44) of the disc portion (7). Alternatively, air holes (50) are provided in the flange portion (22) in the form of circumferential slots for covering a plurality of radial holes to feed the cooling air homogeneously so that a prior art air separator of an existing plant can be replaced.
摘要翻译： PCT No.PCT / JP98 / 02688 Sec。 371日期1999年2月11日 102（e）1999年2月11日PCT PCT。1998年6月18日PCT公布。公开号WO98 / 59156 日期：1998年12月30日在燃气轮机的空气分离器中，由于微动疲劳，防止在空气分离器的凸缘部发生裂纹。空气分离器（20）具有由两个分离器构件（20-1和20-2）形成的圆柱形分离结构，其中一个分离器（20-1）安装在转子（1）上，而另一个分隔件（20-2）通过延伸穿过形成在凸缘部分（22）中的螺栓孔（23）的螺栓（28）安装在活动叶片（2）侧上的盘部分（7）上。来自压缩机的冷却空气从管道（5）进入空间（6）并从间隙（33）传递到通道（32），从而将其供给到空气供给孔（43）和径向孔盘部（7）。或者，空气孔（50）以周向槽的形式设置在凸缘部分（22）中，用于覆盖多个径向孔，以均匀地供给冷却空气，使得可以更换现有设备的现有技术的空气分离器。

9. 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。

10. 发明授权

US6092983A 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：US6092983A
公开(公告)日：2000-07-25
申请号：US202594
申请日：1998-12-17
申请人： Yasuoki Tomita , Sunao Aoki , Kiyoshi Suenaga , Tatsuo Ishiguro
发明人： Yasuoki Tomita , Sunao Aoki , Kiyoshi Suenaga , Tatsuo Ishiguro
IPC分类号： F01D5/18 , F01D9/02 , F01D9/06 , F01D9/04
CPC分类号： F01D9/065 , F01D5/187 , F01D9/02 , F05D2240/10 , F05D2240/81 , F05D2260/22141
摘要： In a cooled stationary blade assembly for a gas turbine, an interior of a blade and an inner shroud are cooled by steam to eliminate the use of air cooling. Steam passages 33A, 33B, 33C, 33D, 33E and 33F are provided in the stationary blade 30. The cooling steam 39 is introduced from the steam passage 33A on the front edge side through an outer shroud and passes, in order, through the steam passages 33B, 33C, 33D, and 33E to flow into the steam passage 33F at the rear edge side to cool the interior of the blade, and is recovered through the outer shroud from the upper portion of the steam passage 33F. A portion of the steam from the steam passage 33A is introduced into the inner shroud 31, enters to steam passages 20 from a steam introduction passage 22, branches to the right and left through both end portions, and flows out into the steam passage 33F at the rear edge from a steam discharge passage 21. Not only the interior of the blade, but also the interior of the inner shroud 31 is cooled by the steam so that the cooling air is dispensed with.
摘要翻译： PCT No.PCT / JP98 / 01958 371日期1998年12月17日第 102（e）1998年12月17日日期PCT提交1998年4月28日PCT公布。出版物WO98 / 50684 日期1998年11月12日在用于燃气轮机的冷却固定叶片组件中，叶片和内罩的内部由蒸汽冷却以消除空气冷却的使用。蒸汽通道33A，33B，33C，33D，33E和33F设置在固定叶片30中。冷却蒸汽39通过外护罩从前边缘侧的蒸汽通道33A引入，并依次通过蒸汽通道33B，33C，33D和33E在后边缘侧流入蒸汽通道33F以冷却叶片的内部，并通过外护罩从蒸汽通道33F的上部回收。来自蒸汽通道33A的蒸汽的一部分被引入内罩31，从蒸汽引入通道22进入蒸汽通道20，通过两个端部向右和向左分支，并且流出到蒸汽通道33F中来自蒸汽排出通道21的后边缘。不仅叶片的内部，而且内部护罩31的内部都被蒸汽冷却，从而省去了冷却空气。

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