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公开(公告)号：US06758651B2
公开(公告)日：2004-07-06
申请号：US10270639
申请日：2002-10-16
IPC分类号： F01D906
CPC分类号： F01D5/18 , F01D25/12 , Y02T50/676
摘要： A gas turbine wherein cooling failure attributable to the occurrence of a horseshoe vortex produced in the vicinity of the stationary blades of the turbine is preventable, the gas turbine including moving blades provided on a rotor side which rotate together with the rotor, and stationary blades provided on a stationary side which cover the periphery of the moving blades and form a combustion gas flow path in the interior, and which are arranged alternately with the moving blades in the rotation axis direction of the rotor.
摘要翻译： 一种燃气轮机，其中由于在涡轮机的静止叶片附近产生的马蹄涡涡发生的冷却故障是可预防的，包括设置在与转子一起旋转的转子侧上的动叶片和设置的固定刀片 在固定侧上覆盖活动叶片的周边并在内部形成燃烧气体流路，并且与转动叶片的旋转轴线方向交替配置。
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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.
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公开(公告)号：US06290462B1
公开(公告)日：2001-09-18
申请号：US09272559
申请日：1999-03-19
申请人： Tatsuo Ishiguro , Koji Watanabe , Masaaki Matsuura , Kenichiro Takeishi , Junichiro Masada , Yasuoki Tomita , Kiyoshi Suenaga
发明人： Tatsuo Ishiguro , Koji Watanabe , Masaaki Matsuura , Kenichiro Takeishi , Junichiro Masada , Yasuoki Tomita , Kiyoshi Suenaga
IPC分类号： F01D1100
CPC分类号： F01D5/187 , F05D2250/185 , F05D2260/2212
摘要： A gas turbine cooled blade is constructed without an increase in the number of parts or time requirements, in which seal air is maintained at a lower temperature with the heat exchange rate being suppressed, and the heat transfer rate of the cooling medium in cooling passage is enhanced. A plurality of cooling passages (A, B, C, D, E) is provided in a blade, and the first row cooling passage (A) is covered at the blade inner and outer peripheries and communicates with the second row cooling passage (B) through communication holes (6) and with the main flow gas path through film cooling holes (7). The second row cooling passage (B) communicates with the blade inner peripheral cavity (10) to form a seal air supply passage. A plurality of ribs (31) are disposed on the inner wall of cooling passage (22) with a predetermined pitch (P). The ribs are arranged alternately and are inclined against cooling medium flow with respective higher first end contacting lower side faces of an immediately upstream rib at a position on both side portions of cooling passage (22). High heat transfer rate areas are formed on both side portions of cooling passage (22), and the average heat transfer rate in cooling passage is enhanced.
摘要翻译： 在不增加部件或时间要求的情况下构建燃气轮机冷却叶片，其中密封空气在热交换率被抑制下保持在较低温度，并且冷却通道中的冷却介质的传热速率为 增强。 多个冷却通道（A，B，C，D，E）设置在叶片中，第一排冷却通道（A）被覆盖在叶片的内周和外周，并与第二排冷却通道 ）通过连通孔（6）并且主流动气体通道通过膜冷却孔（7）。 第二排冷却通道（B）与叶片内周腔（10）连通，形成密封空气供给通道。 多个肋（31）以预定的间距（P）设置在冷却通道（22）的内壁上。 这些肋交替布置并且相对于冷却介质流倾斜，并且在冷却通道（22）的两侧部分的位置处，相应较高的第一端接触紧紧上游的肋的下侧面。 在冷却通道（22）的两侧形成有高的传热率区域，并且冷却通路的平均传热率提高。
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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
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.
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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
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。
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公开(公告)号：US06092991A
公开(公告)日：2000-07-25
申请号：US35500
申请日：1998-03-05
申请人： Yasuoki Tomita , Taku Ichiryu , Kiyoshi Suenaga
发明人： Yasuoki Tomita , Taku Ichiryu , Kiyoshi Suenaga
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F05D2240/81 , F05D2260/2212
摘要： A gas turbine blade having a platform and a turbine wheel plate, in which cooling passages are arranged in a plurality of rows and connected to one another in a blade trunk section of a moving blade and a supply-side passage and a discharge-side passage are formed in a blade root section. The gas turbine blade comprises a pocket having an inlet and an outlet formed in the blade root section. The supply-side passage is connected to one of the cooling passages and the inlet of the pocket, the outlet of the pocket is connected to another of the cooling passages, and the discharge-side passage is connected to one of the cooling passages other than the ones connected individually to the supply-side passage and the pocket.
摘要翻译： 一种具有平台和涡轮机叶轮板的燃气轮机叶片，其中，冷却通道以多行排列并且在动叶片的叶片主干部分和供给侧通道和排出侧通道中彼此连接 形成在叶片根部中。 燃气轮机叶片包括具有形成在叶片根部中的入口和出口的袋。 供给侧通路连接到一个冷却通道和袋的入口，口袋的出口连接到另一个冷却通道，排出侧通道连接到除了 它们分别连接到供应侧通道和口袋。
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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
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。
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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
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。
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公开(公告)号：US07168914B2
公开(公告)日：2007-01-30
申请号：US11246227
申请日：2005-10-11
IPC分类号： F01D9/06
CPC分类号： F01D11/005 , B23K26/389 , F01D5/18 , F01D5/187 , F01D5/188 , F01D9/041 , F05D2240/80 , F05D2240/81 , F05D2260/201 , F05D2260/2212
摘要： The gas turbine stationary blade comprises a stationary blade section provided therein with a passage for cooling air, an inner shroud for supporting the stationary blade section on the side of a discharge port of the cooling air, and a plurality of segments each of which includes at least one stationary blade section and at least one inner shroud. A flow passage is pulled out from the discharge port of the cooling air, and the flow passage is introduced to a front edge corner section of the inner shroud and is extended rearward along a side edge of the inner shroud.
摘要翻译： 燃气轮机固定叶片包括设置有用于冷却空气的通道的固定叶片部分，用于在冷却空气的排出口的侧面支撑固定叶片部分的内护罩，以及多个部分，每个部分包括在 至少一个固定叶片部分和至少一个内部护罩。 流动通道从冷却空气的排出口被拉出，并且流动通道被引入内护罩的前边缘角部并且沿内护罩的侧边缘向后延伸。
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公开(公告)号：US20060177301A1
公开(公告)日：2006-08-10
申请号：US11246227
申请日：2005-10-11
IPC分类号： F03B11/00
CPC分类号： F01D11/005 , B23K26/389 , F01D5/18 , F01D5/187 , F01D5/188 , F01D9/041 , F05D2240/80 , F05D2240/81 , F05D2260/201 , F05D2260/2212
摘要： The gas turbine stationary blade comprises a stationary blade section provided therein with a passage for cooling air, an inner shroud for supporting the stationary blade section on the side of a discharge port of the cooling air, and a plurality of segments each of which includes at least one stationary blade section and at least one inner shroud. A flow passage is pulled out from the discharge port of the cooling air, and the flow passage is introduced to a front edge corner section of the inner shroud and is extended rearward along a side edge of the inner shroud.
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