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公开(公告)号：US08137056B2
公开(公告)日：2012-03-20
申请号：US12281369
申请日：2007-02-26
申请人： Shu Fujimoto , Youji Ohkita , Yoshitaka Fukuyama , Takashi Yamane , Masahiro Matsushita , Toyoaki Yoshida
发明人： Shu Fujimoto , Youji Ohkita , Yoshitaka Fukuyama , Takashi Yamane , Masahiro Matsushita , Toyoaki Yoshida
IPC分类号： F04D31/00
CPC分类号： F01D25/246 , F01D11/08 , F01D11/24 , F05D2240/11 , F05D2260/201 , F05D2260/202 , F05D2260/2212 , F05D2260/2214
摘要： An impingement cooled structure includes a plurality of shroud members disposed in a circumferential direction to constitute a ring-shaped shroud surrounding a hot gas stream, and a shroud cover mounted on radial outside faces of the shroud members to form a cavity therebetween. The shroud cover has a first impingement cooling hole which communicates with the cavity and allows cooling air to be jetted to an inside thereof so as to cool an inner surface of the cavity by impingement. The shroud members each has a hole fin. The hole fin divides the cavity into a plurality of sub-cavities. Further, the hole fin has a second impingement cooling hole which allows the cooling air having flowed through the first impingement cooling hole to be jetted obliquely toward a bottom surface of the sub-cavity adjacent thereto.
摘要翻译： 冲击冷却结构包括沿圆周方向设置的多个护罩构件，以构成围绕热气流的环形罩，以及安装在护罩构件的径向外表面上以在其间形成空腔的罩盖。 护罩盖具有与空腔连通的第一冲击冷却孔，并允许将冷却空气喷射到其内部，以便通过冲击来冷却腔的内表面。 护罩构件各自具有孔翅片。 孔鳍将空腔分成多个子腔。 此外，孔翅片具有第二冲击冷却孔，其允许流过第一冲击冷却孔的冷却空气倾斜地朝与其相邻的子腔的底表面喷射。
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公开(公告)号：US20090035125A1
公开(公告)日：2009-02-05
申请号：US12281369
申请日：2007-02-26
申请人： Shu Fujimoto , Youji Ohkita , Yoshitaka Fukuyama , Takashi Yamane , Masahiro Matsushita , Toyoaki Yoshida
发明人： Shu Fujimoto , Youji Ohkita , Yoshitaka Fukuyama , Takashi Yamane , Masahiro Matsushita , Toyoaki Yoshida
CPC分类号： F01D25/246 , F01D11/08 , F01D11/24 , F05D2240/11 , F05D2260/201 , F05D2260/202 , F05D2260/2212 , F05D2260/2214
摘要： An impingement cooled structure includes a plurality of shroud members disposed in a circumferential direction to constitute a ring-shaped shroud surrounding a hot gas stream, and a shroud cover mounted on radial outside faces of the shroud members to form a cavity therebetween. The shroud cover has a first impingement cooling hole which communicates with the cavity and allows cooling air to be jetted to an inside thereof so as to cool an inner surface of the cavity by impingement. The shroud members each has a hole fin. The hole fin divides the cavity into a plurality of sub-cavities. Further, the hole fin has a second impingement cooling hole which allows the cooling air having flowed through the first impingement cooling hole to be jetted obliquely toward a bottom surface of the sub-cavity adjacent thereto.
摘要翻译： 冲击冷却结构包括沿圆周方向设置的多个护罩构件，以构成围绕热气流的环形罩，以及安装在护罩构件的径向外表面上以在其间形成空腔的罩盖。 护罩盖具有与空腔连通的第一冲击冷却孔，并允许将冷却空气喷射到其内部，以便通过冲击来冷却腔的内表面。 护罩构件各自具有孔翅片。 孔鳍将空腔分成多个子腔。 此外，孔翅片具有第二冲击冷却孔，其允许流过第一冲击冷却孔的冷却空气倾斜地朝与其相邻的子腔的底表面喷射。
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公开(公告)号：US08172505B2
公开(公告)日：2012-05-08
申请号：US12279452
申请日：2007-02-07
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F01D9/041 , F05D2250/185 , F05D2250/314 , F05D2250/70 , F05D2260/202 , F05D2260/2212 , F05D2260/22141
摘要： In this cooling structure, a cooling flow path, which is meandering around a flow direction of a high temperature combustion gas, is provided in a structural body. The cooling flow path has an inflow path for a cooling air formed inside of the structural body; at least one straight flow path provided with intervals with respect to an axial line; and a turning flow path for communicating the end portions of the inflow path with the straight flow path or communicating with the end portions of the straight flow paths one after another.
摘要翻译： 在这种冷却结构中，在结构体中设置有围绕高温燃烧气体的流动方向曲折的冷却流路。 冷却流路具有形成在结构体内部的冷却空气的流入路径， 至少一个相对于轴线设置间隔的直流道; 以及用于使流入路径的端部与直流路连通或者与直流路径的端部相互连通的回转流路。
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公开(公告)号：US20090126335A1
公开(公告)日：2009-05-21
申请号：US12279452
申请日：2007-02-07
CPC分类号： F01D5/187 , F01D9/041 , F05D2250/185 , F05D2250/314 , F05D2250/70 , F05D2260/202 , F05D2260/2212 , F05D2260/22141
摘要： In this cooling structure, a cooling flow path, which is meandering around a flow direction of a high temperature combustion gas, is provided in a structural body. The cooling flow path has an inflow path for a cooling air formed inside of the structural body; at least one straight flow path provided with intervals with respect to an axial line; and a turning flow path for communicating the end portions of the inflow path with the straight flow path or communicating with the end portions of the straight flow paths one after another.
摘要翻译： 在这种冷却结构中，在结构体中设置有围绕高温燃烧气体的流动方向曲折的冷却流路。 冷却流路具有形成在结构体内部的冷却空气的流入路径， 至少一个相对于轴线设置间隔的直流道; 以及用于使流入路径的端部与直流路连通或者与直流路径的端部相互连通的回转流路。
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公开(公告)号：US20130108471A1
公开(公告)日：2013-05-02
申请号：US13808641
申请日：2011-07-07
申请人： Shu Fujimoto
发明人： Shu Fujimoto
IPC分类号： F01D5/18
CPC分类号： F01D5/182 , F01D5/186 , F05D2250/185 , Y02T50/673 , Y02T50/676
摘要： A turbine blade that is used in a turbine of a gas turbine engine and cooled by cooling air, and includes a cooling channel that is formed within the turbine blade and in which the cooling air flows, plural bottomed recesses that are formed on a blade surface of the turbine blade and of which each downstream-side inner wall is inclined, and an ejection hole that is formed on each bottom of the plural bottomed recesses and communicates with the cooling channel to eject the cooling air. The ejection hole is formed so that a central line of the ejection hole extends along the downstream-side inner wall. The above turbine blade can improve cooling without reducing efficiency.
摘要翻译： 一种涡轮叶片，其用于燃气涡轮发动机的涡轮机并由冷却空气冷却，并且包括形成在涡轮机叶片内并且冷却空气流动的冷却通道，形成在叶片表面上的多个有底凹部 并且每个下游侧内壁倾斜的喷射孔和形成在多个有底凹部的每个底部上并与冷却通道连通以喷射冷却空气的喷射孔。 喷射孔形成为使得喷射孔的中心线沿着下游侧内壁延伸。 上述涡轮叶片可以改善冷却而不降低效率。
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公开(公告)号：US20120201694A1
公开(公告)日：2012-08-09
申请号：US13501519
申请日：2010-10-07
申请人： Chiyuki Nakamata , Shu Fujimoto
发明人： Chiyuki Nakamata , Shu Fujimoto
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F05D2230/211 , F05D2240/122 , F05D2240/304 , F05D2250/185 , F05D2260/2214 , F05D2260/22141 , Y02T50/673 , Y02T50/676
摘要： Disclosed is a turbine blade capable of being cooled by a coolant gas supplied to a hollow region, wherein a plurality of meandering flow paths that guide the coolant gas between the suction wall surface and the pressure wall surface while causing the coolant gas to repeatedly meander are continuously arranged from the hub side toward the tip side of the turbine blade, and the meandering flow paths adjacent to each other cause the coolant gas to meander in different repetitive patterns.
摘要翻译： 公开了一种能够被供应到中空区域的冷却剂气体冷却的涡轮叶片，其中在使冷却剂气体重复弯曲的同时在吸入壁表面和压力壁表面之间引导冷却剂气体的多个曲折流动路径是 从轮毂侧朝向涡轮叶片的前端侧连续排列，并且彼此相邻的曲折流动路径使得冷却剂气体以不同的重复图案曲折。
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公开(公告)号：US09194236B2
公开(公告)日：2015-11-24
申请号：US13501519
申请日：2010-10-07
申请人： Chiyuki Nakamata , Shu Fujimoto
发明人： Chiyuki Nakamata , Shu Fujimoto
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F05D2230/211 , F05D2240/122 , F05D2240/304 , F05D2250/185 , F05D2260/2214 , F05D2260/22141 , Y02T50/673 , Y02T50/676
摘要： Disclosed is a turbine blade capable of being cooled by a coolant gas supplied to a hollow region, wherein a plurality of meandering flow paths that guide the coolant gas between the suction wall surface and the pressure wall surface while causing the coolant gas to repeatedly meander are continuously arranged from the hub side toward the tip side of the turbine blade, and the meandering flow paths adjacent to each other cause the coolant gas to meander in different repetitive patterns.
摘要翻译： 公开了一种能够被供应到中空区域的冷却剂气体冷却的涡轮叶片，其中在使冷却剂气体重复弯曲的同时在吸入壁表面和压力壁表面之间引导冷却剂气体的多个曲折流动路径是 从轮毂侧朝向涡轮叶片的前端侧连续排列，并且彼此相邻的曲折流动路径使得冷却剂气体以不同的重复图案曲折。
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公开(公告)号：US09376919B2
公开(公告)日：2016-06-28
申请号：US13808641
申请日：2011-07-07
申请人： Shu Fujimoto
发明人： Shu Fujimoto
IPC分类号： F01D5/18
CPC分类号： F01D5/182 , F01D5/186 , F05D2250/185 , Y02T50/673 , Y02T50/676
摘要： A turbine blade that is used in a turbine of a gas turbine engine and cooled by cooling air, and includes a cooling channel that is formed within the turbine blade and in which the cooling air flows, plural bottomed recesses that are formed on a blade surface of the turbine blade and of which each downstream-side inner wall is inclined, and an ejection hole that is formed on each bottom of the plural bottomed recesses and communicates with the cooling channel to eject the cooling air. The ejection hole is formed so that a central line of the ejection hole extends along the downstream-side inner wall. The above turbine blade can improve cooling without reducing efficiency.
摘要翻译： 一种涡轮叶片，其用于燃气涡轮发动机的涡轮机并由冷却空气冷却，并且包括形成在涡轮机叶片内并且冷却空气流动的冷却通道，形成在叶片表面上的多个有底凹部 并且每个下游侧内壁倾斜的喷射孔和形成在多个有底凹部的每个底部上并与冷却通道连通以喷射冷却空气的喷射孔。 喷射孔形成为使得喷射孔的中心线沿着下游侧内壁延伸。 上述涡轮叶片可以改善冷却而不降低效率。
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