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公开(公告)号：US20100221122A1
公开(公告)日：2010-09-02
申请号：US11507119
申请日：2006-08-21
CPC分类号： F01D5/20 , F05D2250/712 , Y02T50/673
摘要： A turbine blade includes an airfoil terminating in a tip. The tip includes a first rib conforming with a concave pressure side of the airfoil, and a second rib conforming with a convex suction side of the airfoil. The second rib is flared outwardly from the suction side.
摘要翻译： 涡轮机叶片包括终止于尖端的翼型件。 尖端包括符合翼型件的凹入压力侧的第一肋条和与翼型件的凸形吸入侧相一致的第二肋条。 第二肋从吸力侧向外张开。
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公开(公告)号：US20100158696A1
公开(公告)日：2010-06-24
申请号：US12344058
申请日：2008-12-24
申请人： Vidhu Shekhar Pandey , Ching-Pang Lee , Jan Christopher Schilling , Aspi Rustom Wadia , Brian David Keith , Jeffrey Donald Clements
发明人： Vidhu Shekhar Pandey , Ching-Pang Lee , Jan Christopher Schilling , Aspi Rustom Wadia , Brian David Keith , Jeffrey Donald Clements
IPC分类号： F01D5/14
CPC分类号： F01D5/145 , F01D5/143 , F01D5/3007 , F05D2240/80 , F05D2270/17 , Y02T50/673
摘要： A turbine blade includes an airfoil and integral platform at the root thereof. The platform is contoured in elevation from a ridge to a trough, and is curved axially to complement the next adjacent curved platform.
摘要翻译： 涡轮机叶片包括在其根部处的翼型件和整体式平台。 该平台的立面从脊到波纹形状，并且轴向弯曲以补充下一个相邻的弯曲平台。
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公开(公告)号：US07607893B2
公开(公告)日：2009-10-27
申请号：US11507132
申请日：2006-08-21
IPC分类号： F01D5/20
CPC分类号： F01D5/20 , F01D5/145 , F05D2250/70 , Y02T50/671 , Y02T50/673
摘要： A turbine blade includes an airfoil having first and second tip ribs extending along the opposite pressure and suction sides thereof. The tip ribs are spaced apart between the leading and trailing edges of the airfoil to include a tip baffle. The baffle extends chordally in counter profile with the first rib to define a first pocket, and in counter profile with the second rib to define a second pocket.
摘要翻译： 涡轮叶片包括具有沿其相对的压力和吸力侧延伸的第一和第二末端肋的翼型件。 末端肋在翼型件的前缘和后缘之间间隔开，以包括顶端挡板。 所述挡板以第一肋条与第一肋条相反地延伸，以相反轮廓延伸，以限定第一凹槽，并且与第二肋条对置形成第二凹槽。
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公开(公告)号：US07497663B2
公开(公告)日：2009-03-03
申请号：US11586952
申请日：2006-10-26
IPC分类号： F01D5/14
CPC分类号： F01D5/141 , F05D2250/74 , Y10S416/02
摘要： An airfoil for a rotor blade including an uncoated profile substantially in accordance with Cartesian coordinate values of X, Y and Z to facilitate balancing performance and durability of the rotor blade and to facilitate improving an operating efficiency of a high-pressure turbine is provided. The profile is carried only to four decimal places, wherein Y represents a distance from a platform on which the airfoil is mounted, and X and Z are coordinates defining the profile at each distance Y from the platform.
摘要翻译： 提供了一种用于转子叶片的翼型件，其包括基本上根据X，Y和Z的笛卡尔坐标值的未涂覆轮廓，以便于平衡转子叶片的性能和耐久性，并且有助于提高高压涡轮机的操作效率。 配置文件仅承载四位小数，其中Y表示与安装有翼型件的平台的距离，X和Z是从平台每个距离Y定义轮廓的坐标。
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公开(公告)号：US20080118363A1
公开(公告)日：2008-05-22
申请号：US11602421
申请日：2006-11-20
IPC分类号： F01D5/18
CPC分类号： F01D5/20 , F01D5/187 , F05D2250/185 , F05D2250/70 , F05D2260/202 , Y02T50/673 , Y02T50/676
摘要： A turbine blade includes an airfoil having first and second tip ribs extending along the opposite pressure and suction sides thereof. The tip ribs are spaced apart between the leading and trailing edges of the airfoil to include a trifurcate tip baffle defining a triforial tip cavity.
摘要翻译： 涡轮叶片包括具有沿其相对的压力和吸力侧延伸的第一和第二末端肋的翼型件。 末端肋在翼型件的前缘和后缘之间间隔开，以包括限定三腔尖端腔的三尖头挡板。
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