公开(公告)号：US20050013692A1

公开(公告)日：2005-01-20

申请号：US10620365

申请日：2003-07-17

申请人： Daniel Snook ,  Peter Cleveland

发明人： Daniel Snook ,  Peter Cleveland

IPC分类号： F01D5/14 ,  F01D5/20 ,  F01D5/22 ,  B63H1/16

CPC分类号： F01D5/225 ,  F05D2250/70

摘要： A turbine bucket includes a bucket airfoil having a tip shroud with leading and trailing edges defining leading and trailing edge profiles substantially in accordance with Cartesian coordinate values of X and Y at points 12-20 and 1-11, respectively, set forth in Table I. The X and Y values are distances in inches which, when respective points 12-20 and 1-11 are connected by smooth, continuing arcs, define the leading and trailing edge tip shroud profiles. An airfoil profile at 95% span is defined by Cartesian coordinate values of X, Y and Z in Table II having the same X, Y origin along the radial Z axis as the origin of Table I. The profiled leading and trailing edges of the tip shroud relative to the airfoil profile afford optimum tip shroud mass distribution which maximizes creep life of the bucket. Stage efficiency is also improved by providing a tip shroud covering the airfoil throat.

摘要翻译： 涡轮机桶包括具有尖端护罩的铲斗翼型件，其前缘和后缘基本上根据表I中所示的点12-20和1-11处的X和Y的笛卡尔坐标值来定义前缘和后缘轮廓 X和Y值是以英寸为单位的距离，当各个点12-20和1-11通过平滑连续的弧连接时，可以定义前缘和后缘尖端护罩轮廓。 95％跨度的翼型轮廓由表II中的X，Y和Z的笛卡尔坐标值定义为具有相同的X，Y原点沿着径向Z轴作为表I的原点。尖端的成型前缘和后缘 相对于翼型轮廓的护罩提供最佳的尖端护罩质量分布，其最大化铲斗的蠕变寿命。 通过提供覆盖翼型喉部的尖端护罩也提高了阶段效率。

公开(公告)号：US20050106025A1

公开(公告)日：2005-05-19

申请号：US10655623

申请日：2003-09-05

申请人： Daniel Snook ,  Peter Cleveland

发明人： Daniel Snook ,  Peter Cleveland

IPC分类号： B63H1/16 ,  F01D5/14

CPC分类号： F01D5/225 ,  F01D5/141 ,  F05D2250/14 ,  F05D2250/16 ,  F05D2250/17 ,  F05D2250/232 ,  F05D2250/70 ,  F05D2250/74

摘要： A turbine bucket airfoil has a conical fillet about the intersection of the airfoil tip and tip shroud having a nominal profile in accordance with coordinate values of X and Y, offset 1, offset 2 and Rho set forth in Table I. The shape parameters of offset 1, offset 2 and Rho define the configuration of the fillet at the specified X and Y locations about the fillet to provide a fillet configuration accommodating high localized stresses. The fillet shape may be parabolic, elliptical or hyperbolic as a function of the value of the shape parameter ratio of D1 D1 + D2 at each X, Y location where D1 is a distance between an intermediate point along a chord between edge points determined by offsets O1 and O2 and a shoulder point on the fillet surface and D2 is a distance between the shoulder point and an apex location at the intersection of the airfoil tip and tip shroud.

摘要翻译： 涡轮叶片翼型件根据X和Y，偏移1，偏移2和Rho的坐标值，具有围绕翼型尖端和尖端护罩的相交处的圆锥形圆角，其具有标称轮廓。偏移量的形状参数 1，偏移2和Rho定义圆角上指定的X和Y位置处的圆角的配置，以提供适应高局部应力的圆角配置。 作为