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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
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。
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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。
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公开(公告)号：US06196798B1
公开(公告)日：2001-03-06
申请号：US09242330
申请日：1999-02-11
IPC分类号： F01D518
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。
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公开(公告)号：US6077034A
公开(公告)日：2000-06-20
申请号：US38451
申请日：1998-03-11
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。
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公开(公告)号：US06190128B1
公开(公告)日：2001-02-20
申请号：US09230942
申请日：1999-02-04
IPC分类号： F01D508
摘要： A cooled moving blade for a gas turbine which has a blade profile capable of more effectively reducing thermal stress in a blade base portion and, thus, preventing cracks from occurring. A moving blade (1) is fixedly secured to a platform (2). On the other hand, a cooling air passage (3) is formed in a serpentine pattern inside of the blade for cooling with cooling air. The moving blade (1) has a base portion of a profile formed by an elliptically curved surface (11) and a rectilinear surface portion (12), wherein the rectilinear surface portion (12) is provided at a hub portion of the blade where thermal stress is large. The cross-sectional area of the blade is increased by providing the rectilinear surface portion (12) The heat capacity is increased, compared with the conventional blade, due to the increased cross-sectional area of the blade. This, in turn, results in a decrease of the temperature difference due to the thermal stress. Thus, the thermal stress can be suppressed more effectively than with the conventional blade.
摘要翻译： 一种用于燃气轮机的冷却的移动叶片，其具有能够更有效地降低叶片基部中的热应力并因此防止裂纹发生的叶片轮廓。 活动叶片（1）固定地固定到平台（2）上。 另一方面，冷却空气通路（3）形成为叶片内的蛇形图案，用冷却空气冷却。 活动叶片（1）具有由椭圆曲面（11）和直线表面部分（12）形成的轮廓的基部，其中直线表面部分（12）设置在叶片的毂部，其中热 压力很大 通过提供直线表面部分（12）来提高叶片的横截面面积。与常规叶片相比，由于叶片的横截面面积增加，热容量增加。 这又导致由于热应力引起的温度差的降低。 因此，与常规叶片相比，可以更有效地抑制热应力。
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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。
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公开(公告)号：US06253537B1
公开(公告)日：2001-07-03
申请号：US09380460
申请日：1999-09-03
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。
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公开(公告)号：US6151881A
公开(公告)日：2000-11-28
申请号：US242293
申请日：1999-02-11
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。
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公开(公告)号：US06578363B2
公开(公告)日：2003-06-17
申请号：US10072865
申请日：2002-02-12
IPC分类号： F02C712
摘要： Cooling air passages are formed in the wall of an exhaust casing connected to a turbine casing of a gas turbine. Low pressure air extracted from the low pressure stage of an air compressor of the gas turbine is supplied to the cooling air passage from the portion near the downstream end of the exhaust casing. Cooling air flows through the cooling air passage toward the upstream end of the exhaust casing and then flows into an annular cavity formed in the turbine casing near the portion corresponding to the last turbine stage. Therefore, the metal temperature of the exhaust casing near the upstream end (near the joint between the exhaust casing and the turbine casing) is lowered by the cooling air and, as cooling air of a relatively high temperature is supplied to the cavity in the turbine casing, the metal temperature of the turbine casing near the downstream end becomes higher than that provided by a conventional cooling system. Therefore, the difference between the metal temperatures of the turbine casing and the exhaust casing becomes very small and the thermal stress exerted on the exhaust casing due to the temperature difference can be largely reduced.
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公开(公告)号：US20110268533A1
公开(公告)日：2011-11-03
申请号：US13178928
申请日：2011-07-08
申请人： Norikazu TEZUKA , Kazuharu Hirokawa , Keisuke Ihara , Kei Osawa , Hiroshi Ishikawa , Taiji Torigoe , Ryuichi Yamamoto , Yukihiro Hashimoto , Nobuyuki Izutsu , Koji Takahashi
发明人： Norikazu TEZUKA , Kazuharu Hirokawa , Keisuke Ihara , Kei Osawa , Hiroshi Ishikawa , Taiji Torigoe , Ryuichi Yamamoto , Yukihiro Hashimoto , Nobuyuki Izutsu , Koji Takahashi
CPC分类号： B24C1/10 , B23G9/001 , B23P9/04 , B23P15/00 , C21D9/0093 , F01D5/066 , F05D2230/311 , F05D2230/90 , F05D2260/941 , F05D2300/211 , F05D2300/2112 , F05D2300/2261 , F16B33/06 , Y10T29/479
摘要： A bolt has a male screw with a surface hardening portion that has an increased surface hardness and that is applied with a compressive residual stress. The male screw is formed by cutting the bolt, and performing a process to provide at least on the surface of the male screw of the bolt the surface hardening portion that has increased hardness and that is applied with a compressive residual stress. As a result, the fatigue resistance of the male screw is improved and the bolt is effective for use in a portion where the male screw is subject to a repetitive stress.
摘要翻译： 螺栓具有具有表面硬化部分的外螺纹，其具有增加的表面硬度并且施加有压缩残余应力。 通过切割螺栓形成外螺纹，并且执行至少在螺栓的外螺纹的表面上提供具有增加的硬度并施加有压缩残余应力的表面硬化部的工艺。 结果，提高了外螺纹的耐疲劳性，并且螺栓对于使用阳螺纹受到重复应力的部分是有效的。
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