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公开(公告)号：US06508623B1
公开(公告)日：2003-01-21
申请号：US09959310
申请日：2001-10-22
申请人： Shigehiro Shiozaki , Yasuoki Tomita
发明人： Shigehiro Shiozaki , Yasuoki Tomita
IPC分类号： F01D1124
CPC分类号： F01D25/12 , F01D9/04 , F01D11/08 , F01D25/246 , F05D2260/201
摘要： A gas turbine segmental ring has an increased rigidity to suppress a thermal deformation and enables less cooling air leakage by less number of connecting portions of segment structures. Cooling air (70) from a compressor flows through cooling holes (61) of an impingement plate (60) to enter a cavity (62) and to impinge on a segmental ring (1) for cooling thereof. The cooling air (70) further flows into cooling passages (64) from openings (63) of the cavity (62) for cooling an interior of the segmental ring (1) and is discharged into a gas path from openings of a rear end of the segmental ring (1). Waffle pattern (10) of ribs arranged in a lattice shape is formed on an upper surface of the segmental ring (1) to thereby increase the rigidity. A plurality of slits (6) are formed in flanges (4, 5) extending in the turbine circumferential direction to thereby absorb the deformation and thermal deformation of the segmental ring (1) is suppressed.
摘要翻译： 燃气轮机节段环具有增加的刚性以抑制热变形，并且通过较少数量的节段结构的连接部分能够减少冷却空气泄漏。 来自压缩机的冷却空气（70）流过冲击板（60）的冷却孔（61）进入空腔（62）并撞击节段环（1）以进行冷却。 冷却空气（70）进一步从空腔（62）的开口（63）流入冷却通道（64），用于冷却节段环（1）的内部，并从其后端的开口排出气体通道 节段环（1）。 排列成格子状的肋的楔形花纹（10）形成在节段环（1）的上表面上，从而增加刚性。 多个狭缝（6）形成在沿涡轮机圆周方向延伸的凸缘（4,5）中，从而吸收变形，并且抑制了节段环（1）的热变形。
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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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公开(公告)号：US20050135925A1
公开(公告)日：2005-06-23
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.
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5.发明授权Turbine moving blade, turbine stationary blade, turbine split ring, and gas turbine 有权涡轮动叶片，涡轮固定叶片，涡轮分裂环和燃气轮机公开(公告)号：US06811373B2
公开(公告)日：2004-11-02
申请号：US10067947
申请日：2002-02-08
IPC分类号： F01D518
CPC分类号： F01D5/288 , C23C28/00 , F01D9/02 , F05D2230/90 , F05D2240/80 , F05D2300/611
摘要： The present invention provides a turbine moving blade, a turbine stationary blade, and a turbine split ring which are capable of restraining the deterioration and peeling-off of a thermal barrier coating easily and surely, and a gas turbine capable of enhancing the energy efficiency by increasing the temperature of combustion gas. The turbine moving blade provided in a turbine constituting the gas turbine includes a platform having a gas path surface extending in the combustion gas flow direction, and a blade portion erecting on the platform. The thermal barrier coating covering the gas path surface is formed so as to go around from the gas path surface to an upstream-side end face and a downstream-side end face of the outer peripheral faces of the platform.
摘要翻译： 本发明提供了能够容易且可靠地抑制热障涂层的劣化和剥离的涡轮机动叶片，涡轮静叶片和涡轮分裂环，以及能够通过以下方式提高能量效率的燃气轮机 增加燃烧气体的温度。 设置在构成燃气轮机的涡轮机中的涡轮机动叶片具有在燃烧气体流动方向上具有气体流路面的平台和在平台上竖起的叶片部。 覆盖气体路径表面的隔热涂层形成为从气体路径表面到平台的外周面的上游侧端面和下游侧端面。
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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：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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