公开(公告)号：US20060024168A1

公开(公告)日：2006-02-02

申请号：US10903803

申请日：2004-07-30

申请人： Takao Fukuda ,  Francis Price ,  Shankar Magge

发明人： Takao Fukuda ,  Francis Price ,  Shankar Magge

IPC分类号： B63H1/26

CPC分类号： F01D5/141 ,  F05D2220/3212 ,  F05D2240/301 ,  F05D2250/74 ,  Y10S416/02 ,  Y10S416/05

摘要： Provided is an aerodynamic profile for use in gas turbine airfoil and a turbine blade comprising such profiles. The profiles counteract a reduction in area between adjacent airfoils due to an increase in coating thickness. A plurality of radial sections forms both coated and uncoated nominal profiles of the airfoils. The sections are located within a tolerance measured in any direction perpendicular to an airfoil stacking line extending radially from a central axis and defined by X, Y, and R Cartesian coordinate values in inches. The R values are measured perpendicular to a plane normal to the airfoil stacking line with R values of zero at a lowermost radial section and increasing in the radial direction. The X and Y values are measured perpendicular to the airfoil stacking line.

摘要翻译： 提供用于燃气涡轮机翼型件的空气动力学特性和包括这种轮廓的涡轮叶片。 轮廓由于涂层厚度的增加而抵消相邻翼面之间的面积减小。 多个径向部分形成翼型件的涂覆和未涂覆的标称轮廓。 这些部分位于从垂直于从中心轴线径向延伸并由X，Y和R笛卡尔坐标值以英寸限定的翼型堆叠线的任何方向上测量的公差内。 R值垂直于垂直于翼型堆叠线的平面测量，在最低径向截面处R值为零，并且在径向方向上增加。 垂直于翼型堆叠线测量X和Y值。