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。

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。

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。

公开(公告)号：US6019579A

公开(公告)日：2000-02-01

申请号：US37111

申请日：1998-03-09

申请人： Hiroki Fukuno ,  Yasuoki Tomita ,  Kiyoshi Suenaga

发明人： Hiroki Fukuno ,  Yasuoki Tomita ,  Kiyoshi Suenaga

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

CPC分类号： F01D5/187 ,  F05D2260/22141 ,  F05D2260/2322

摘要： A gas turbine rotating blade comprises a serpentine passage provided in the blade width direction in plural rows in a blade profile portion except the portion near the trailing edge having a small blade thickness, a steam cooling passage provided around the outer periphery of a platform, an air passage provided in the blade width direction in the vicinity of the trailing edge of blade profile portion, an impingement plate provided under the platform on the inside of the steam cooling passage, slot holes formed so as to branch off from the air passage and be directed to the trailing edge, and slits formed in the platform above the impingement plate. Therefore, the blade profile portion is cooled by the steam passing through the serpentine passage and the air passing through the air passage, so that the cooling construction is not complicated, and cooling is performed effectively. For the platform, the outer periphery thereof is cooled by steam and the inside thereof by air effectively.

摘要翻译： 燃气轮机旋转叶片包括沿叶片宽度方向设置的蛇形通道，叶片轮廓部分中除了具有小叶片厚度的后缘附近的部分之外的多个行中，围绕平台的外周设置的蒸汽冷却通道， 在叶片宽度方向上设置在叶片轮廓部分的后缘附近的空气通道，设置在蒸汽冷却通道内侧的平台下方的冲击板，形成为从空气通道分支的槽孔，并且 引导到后缘，以及形成在冲击板上方的平台中的狭缝。 因此，叶片轮廓部分被通过蛇形通道的蒸汽和通过空气通道的空气冷却，使得冷却结构不复杂，并且有效地进行冷却。 对于平台，其外周边由蒸汽及其内部有效地被空气冷却。

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：US06602048B2

公开(公告)日：2003-08-05

申请号：US09998201

申请日：2001-12-03

申请人： Tatsuaki Fujikawa ,  Yasuoki Tomita ,  Shunsuke Torii ,  Ryotaro Magoshi ,  Masamitsu Kuwabara ,  Shinichi Inoue

发明人： Tatsuaki Fujikawa ,  Yasuoki Tomita ,  Shunsuke Torii ,  Ryotaro Magoshi ,  Masamitsu Kuwabara ,  Shinichi Inoue

IPC分类号： F01D1124

CPC分类号： F01D11/08 ,  F01D9/00 ,  F01D11/18 ,  F05D2250/181 ,  F05D2250/282 ,  F05D2260/201 ,  F05D2260/30

摘要： In the gas turbine split ring, on an outer peripheral surface 1b between two cabin attachment flanges, a circumferential rib which extends in the circumferential direction and an axial rib which extends in the axial direction and has a height taller than that of the circumferential rib are, respectively, formed in plural lines, so that it is possible to suppress heat deformation in the axial direction which largely contributes to reduction of the tip clearance compared to head deformation in the circumferential direction more efficiently.

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：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：US6089827A

公开(公告)日：2000-07-18

申请号：US242108

申请日：1999-02-09

申请人： Taku Ichiryu ,  Koichi Akagi ,  Yasuoki Tomita

发明人： Taku Ichiryu ,  Koichi Akagi ,  Yasuoki Tomita

IPC分类号： F01D5/06 ,  F01D5/08 ,  F01D11/00 ,  B63H1/00

CPC分类号： F01D5/066 ,  F01D11/005 ,  F01D5/084

摘要： A gas turbine rotor, in which a plurality of discs having teeth of a bevel gear are juxtaposed to engage the teeth and are integrally fastened by a bolt extending through the discs, so that the discs may be cooled by feeding cooling air to the air passages of the individual discs sequentially at the running time, is provided whereby the cooling air is prevented from leaking by means having no wear. Radially outward of an air passage through hole of the faces of the adjoining discs, there are provided arms which are made lower than the dedendums of the teeth and protruded in an annular shape to confront each other; one of the arms has a tip made to have an elastically deformable thickness and a sectional shape bent inward or outward, whereas there is welded to the other arm an extension which has a tip made to have an elastically deformable thickness and a sectional shape bent inward or outward; and the end face of the tip of the one arm and the end face of the tip of the extension of the other arm are held in abutment against each other so that the two end faces may be forced, when the discs are integrated, into contact with each other to prevent leakage of cooling air.

摘要翻译： PCT No.PCT / JP98 / 02564 Sec。 371日期1999年2月9日 102（e）1999年2月9日PCT PCT 1996年6月10日PCT公布。 第WO98 / 57040号公报 日期1998年12月17日一种燃气轮机转子，其中具有锥齿轮齿的多个盘并列配合以接合齿，并且通过延伸穿过盘的螺栓一体地紧固，使得盘可以通过进给冷却来冷却 提供了在运行时间顺序地对各个盘的空气通道的空气，由此通过没有磨损的装置防止冷却空气泄漏。 设置在相邻盘的表面的空气通道通孔的径向外侧，设置有比齿的齿根低的突出的环状并相互对置的臂。 其中一个臂具有制成具有可弹性变形的厚度和向内或向外弯曲的截面形状的尖端，而焊接到另一个臂的延伸部，该延伸部具有制成具有可弹性变形的厚度和向内弯曲的截面形状 或向外; 并且一个臂的末端的端面和另一个臂的延伸部的末端的端面保持彼此抵靠，使得当盘被一体化时两个端面可能被强制接触 相互防止冷却空气泄漏。

公开(公告)号：US5564902A

公开(公告)日：1996-10-15

申请号：US426187

申请日：1995-04-21

申请人： Yasuoki Tomita

发明人： Yasuoki Tomita

IPC分类号： F01D5/18 ,  F01D5/20 ,  F02C7/18

CPC分类号： F01D5/20 ,  F05D2260/202

摘要： In a gas turbine hollow cooled rotor blade, a plurality of cooling holes 3 and 5 are provided which communicate between a cooling air passage in the blade and the tip squealer portion 1 on the pressure side and between the cooling air passage in the blade and a position in the vicinity of the suction side of a tip cap 4.

摘要翻译： 在燃气轮机中空冷却转子叶片中，设置有多个冷却孔3和5，它们连接在叶片中的冷却空气通道和压力侧的尖端推进器部分1和叶片中的冷却空气通道之间， 位于尖端盖4的吸力侧附近。