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公开(公告)号：US5846048A
公开(公告)日：1998-12-08
申请号：US862146
申请日：1997-05-22
申请人： Yasuoki Tomita , Taku Ichiryu
发明人： Yasuoki Tomita , Taku Ichiryu
CPC分类号： F01D25/12 , F01D5/187 , F05D2260/205 , F05D2260/2322
摘要： Object: Gas turbine blade cooling is generally made by use of air, which has a limitation in enhancement of a thermal efficiency, so steam as a cooling medium is being studied. In a steam cooling method, however, a secure recovery of cooling steam and a secure prevention of leakage is required. The present invention provides a new unit which can satisfy such requirement. Solving means: There are provided a column extending in a radial direction on an outer periphery of a shroud, a supply passage and a recovery passage of a cooling medium within said column and a means for joining a supply tube and a recovery tube of the cooling medium connected to a starting end of said supply passage and a finishing end of said recovery passage, respectively, at a terminal end portion of said column, thereby the cooling medium supplied via the supply tube and the supply passage is recovered securely via the recovery passage and the recovery tube so that no leakage occurs outside, thus an employment of steam etc. as a cooling medium can be realized.
摘要翻译： 对象：燃气轮机叶片冷却通常通过使用空气来制造，这对于提高热效率具有局限性，因此正在研究作为冷却介质的蒸汽。 然而，在蒸汽冷却方法中，需要安全地回收冷却蒸汽并确保防止泄漏。 本发明提供能够满足这种要求的新单元。 解决方案：提供了一个在径向方向上延伸的柱体，该柱体在护罩的外周边，供应通道和所述塔内的冷却介质的回收通道和用于连接供应管和冷却回收管的装置 介质在所述塔的末端部分别连接到所述供应通道的起始端和所述回收通道的末端，由此经由供应管和供给通道供应的冷却介质经由回收通道 和回收管，使得不会在外部发生泄漏，因此可以实现作为冷却介质的蒸汽等的使用。
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公开(公告)号：US5785496A
公开(公告)日：1998-07-28
申请号：US803771
申请日：1997-02-24
申请人： Yasuoki Tomita
发明人： Yasuoki Tomita
CPC分类号： F01D5/187 , F01D5/225 , F05D2240/81
摘要： A gas turbine rotor blade includes a shroud which is cooled effectively with cooling gas used for cooling the blade profile so that the temperature of the shroud is reduced and the life of the gas turbine rotor blade is extended. A two-step groove is engraved in the shroud along the tip of the blade profile and the upper portion of the two-step groove is plugged. Second cooling holes are bored along the direction of the plane of the shroud so as to be connected to and communicate with the first cooling holes which are bored in the blade profile in a direction along the longitudinal axis of the blade for passing cooling gas through the blade. Consequently, most of the cooling gas, after cooling the blade profile, can be used for cooling the shroud, so that the shroud is cooled effectively and the temperature thereof is prevented from rising. Preventing the temperature from rising can also prevent reduction of the creep resistance of the shroud and prevent the blade root on the shroud from being turned up.
摘要翻译： 一种燃气涡轮机转子叶片包括用冷却气体冷却冷却叶片轮廓的罩体，从而使护罩的温度降低，燃气轮机转子叶片的寿命延长。 沿着刀片轮廓的尖端刻在护罩中的两步槽，并且两步槽的上部被堵塞。 第二冷却孔沿着护罩的平面方向钻孔，以便沿着沿着刀片的纵向轴线的方向与在叶片轮廓中钻孔的第一冷却孔连接并连通，以使冷却气体通过 刀。 因此，在冷却叶片轮廓之后，大部分冷却气体可用于冷却护罩，从而有效地冷却护罩并且防止其温度升高。 防止温度升高也可以防止护罩的抗蠕变性降低，并防止护罩上的叶片根部翻倒。
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公开(公告)号：US07252477B2
公开(公告)日：2007-08-07
申请号：US11340510
申请日：2006-01-27
申请人： Yasuoki Tomita , Kouji Watanabe , Masamitsu Okuzono , Masaki Ono
发明人： Yasuoki Tomita , Kouji Watanabe , Masamitsu Okuzono , Masaki Ono
IPC分类号： F01D11/00
CPC分类号： F01D5/081 , F01D5/22 , F01D11/008 , F05C2201/0463 , F05C2201/0466 , F05D2250/29 , F05D2260/20 , Y02T50/671 , Y02T50/676 , Y10S416/50
摘要： A rotating blade body is provided that can restrain vibrations of rotating blades effectively. The rotating blade body comprises a rotor disc, a plurality of rotating blades being assembled so as to extend from the outer circumference of the rotor disc in a radial pattern, and sealing pins extending along the direction of the rotating shaft in the gaps between the platforms of the rotating blades being adjacent in a circumferential direction. The sealing pins have a through-hole made therein, penetrating axially from one end surface to the other end surface.
摘要翻译： 提供了可以有效地抑制旋转叶片的振动的旋转叶片体。 旋转叶片本体包括转子盘，多个旋转叶片组装成以径向图案从转子盘的外圆周延伸，并且在平台之间的间隙中沿着旋转轴的方向延伸的密封销 的旋转叶片在圆周方向上相邻。 密封销具有形成在其中的通孔，其从一个端面轴向穿透到另一端面。
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公开(公告)号：US06966750B2
公开(公告)日：2005-11-22
申请号：US10820744
申请日：2004-04-09
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 low 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。 低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：US06893215B2
公开(公告)日：2005-05-17
申请号：US10025593
申请日：2001-12-26
申请人： Masamitsu Kuwabara , Yoshiyuki Morii , Yasuoki Tomita , Shunsuke Torii , Shigehiro Shiozaki , Kotaro Ohshima , Tatsuaki Fujikawa , Ryotaro Magoshi , Shinichi Inoue
发明人： Masamitsu Kuwabara , Yoshiyuki Morii , Yasuoki Tomita , Shunsuke Torii , Shigehiro Shiozaki , Kotaro Ohshima , Tatsuaki Fujikawa , Ryotaro Magoshi , Shinichi Inoue
CPC分类号： F01D11/005 , F01D11/006 , F01D11/008
摘要： The division wall is made up of a plurality of division wall sections forming a passage wall of high temperature gas which are connected in the direction of arrangement of blades to form a wall surface having a roughly circular cross section as a whole, a gas flow restricting structure for preventing high temperature gas from passing through a gap formed at a connecting portion between the division wall sections in the flow direction of the high temperature gas from the opening on the upstream side of the high temperature gas in the gap, or a gas flow restricting structure for preventing the high temperature gas from being embraced in the gap, for example, a sealing member formed into a prism having a T-shape cross section as a whole composed of a plane portion as a sealing portion and a projected portion for filling the gap is provided.
摘要翻译： 分隔壁由多个分隔壁部分构成，形成高温气体的通道壁，其沿着叶片的排列方向连接以形成整个具有大致圆形横截面的壁表面， 结构，用于防止高温气体从形成在高温气体的流动方向上的分隔壁部分之间的连接部分处的间隙从间隙中的高温气体的上游侧的开口或气流 限制结构用于防止高温气体包围在间隙中，例如，形成为具有作为整体的T形横截面的棱镜的密封构件由作为密封部分的平面部分和用于填充的突出部分组成 提供了差距。
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公开(公告)号：US06783323B2
公开(公告)日：2004-08-31
申请号：US10189413
申请日：2002-07-08
IPC分类号： F01D906
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：US06616405B2
公开(公告)日：2003-09-09
申请号：US09998668
申请日：2001-12-03
IPC分类号： F01D900
CPC分类号： F01D25/12 , F01D5/186 , F05D2240/81 , Y10S415/914
摘要： In a cooling structure for a gas turbine, cooling air diffusion holes are formed from inner surface to outer surface of a platform so as to open from high pressure side blade surface of a moving blade offset in a direction toward low pressure side blade surface of adjacent moving blade confronting the high pressure side blade surface, in a direction of primary flow.
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公开(公告)号：US06572335B2
公开(公告)日：2003-06-03
申请号：US09800668
申请日：2001-03-08
IPC分类号： F04D2958
CPC分类号： F01D5/187 , F01D9/041 , F05D2240/81 , F05D2260/22141
摘要： A gas turbine cooled stationary blade has a blade structure and outer and inner shrouds enhancing cooling efficiency and preventing the occurrence of cracks due to thermal stresses. A blade (1) wall thickness, between 75% and 100% of the blade height of a blade leading edge portion, is made thicker, and the blade (1) wall thickness of other portions is made thinner, as compared with a conventional case. Protruding ribs (4) are provided on a blade (1) convex side inner wall between 0% and 100% of the blade height. A blade (1) trailing edge opening portion is made thinner than the conventional case. Outer shroud (2) is provided with cooling passages (5a, 5b) for air flow in both side end portions. Inner shroud (3) is provided with cooling passages (9a, 9b) for air flow and cooling holes (13a, 13b) for air blow in the side end portions. With the blade (1) structure and the shroud (2, 3) cooling passages (5a, 5b, 9a, 9b) and cooling holes (13a, 13b), the cooling effect is enhanced and cracks are prevented from occurring.
摘要翻译： 燃气轮机冷却的固定叶片具有叶片结构，外部和内部护罩提高冷却效率并防止由于热应力引起的裂纹。 叶片（1）的壁厚在叶片前缘部分的叶片高度的75％和100％之间变得更厚，并且其它部分的叶片（1）的壁厚比常规的情况更薄 。 突出肋（4）设置在叶片高度的0％和100％之间的叶片（1）凸侧内壁上。 叶片（1）后缘开口部分比现有技术更薄。 外护罩（2）设置有用于在两个侧端部中的空气流动的冷却通道（5a，5b）。 内护罩（3）设有用于气流的冷却通道（9a，9b）和用于在侧端部吹气的冷却孔（13a，13b）。 利用叶片（1）结构和护罩（2,3）冷却通道（5a，5b，9a，9b）和冷却孔（13a，13b），冷却效果提高，并且防止发生裂纹。
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公开(公告)号：US06533542B2
公开(公告)日：2003-03-18
申请号：US10043201
申请日：2002-01-14
IPC分类号： F01D1108
摘要： A split ring is disposed on an inner wall of a gas turbine casing. The split ring is composed of a plurality of split segments that are arranged on the inner wall of the casing in circumferential direction. A predetermined clearance is formed between the inner face of a split segment and the rotor blade tips. The split segments are arranged so that a predetermined circumferential clearance is formed between the split segments in order to allow the thermal expansion of the segments. A circumferential end face located upstream side of the segments with respect to the direction of the rotor blade rotation is connected to the inner face by a transition face having a surface formed as an inclined plane. The inclined plane prevents the swirl flow caused by the rotating rotor blade from impinging the upstream end face and, thereby, suppresses a temperature rise of the split segment at the upstream end face.
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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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