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1. 发明授权

US07186090B2 Air foil shape for a compressor blade 失效
标题翻译：用于压缩机叶片的气翼形状
公开(公告)号：US07186090B2
公开(公告)日：2007-03-06
申请号：US10986162
申请日：2004-11-12
申请人： Steven Eric Tomberg , Roger Beharrysingh , Timothy E. DeJoris , William J. Miller , Paul Deivernois , Venkata Siva P. Chaluvadi , Adrian Mircea Mistreanu , Michael James Dutka , Nathan S. Race , Jeffrey Boyd , Christopher David McGowan , Peter Gaines Cleveland , Jason Thomas Harrell , Carl G. Schott , John David Stampfli , Ronald Stuart Denmark , Steven Mark Schirle , Jennifer B. Michenfelder , John F. Ryman
发明人： Steven Eric Tomberg , Roger Beharrysingh , Timothy E. DeJoris , William J. Miller , Paul Deivernois , Venkata Siva P. Chaluvadi , Adrian Mircea Mistreanu , Michael James Dutka , Nathan S. Race , Jeffrey Boyd , Christopher David McGowan , Peter Gaines Cleveland , Jason Thomas Harrell , Carl G. Schott , John David Stampfli , Ronald Stuart Denmark , Steven Mark Schirle , Jennifer B. Michenfelder , John F. Ryman
IPC分类号： F01D5/14
CPC分类号： F01D5/141 , F05D2240/301 , Y10S416/02 , Y10S416/05
摘要： An article of manufacture having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in a table. The table selected from the group of tables consisting of TABLES 1S–16S, 1R–17R, and IGV. Wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z in inches. The profile sections at the Z distances being joined smoothly with one another to form a complete airfoil shape.
摘要翻译：一种具有基本上符合表中列出的X，Y和Z的笛卡尔坐标值的公称轮廓的制品。该表从由表1S-16S，1R-17R和IGV组成的表格中选择。其中X和Y是以英寸为单位的距离，当通过平滑连续的弧连接时，以每英寸的距离Z限定翼型轮廓部分。 Z距离处的轮廓部分彼此平滑地连接以形成完整的翼型形状。

2. 发明授权

US06890150B2 Center-located cutter teeth on shrouded turbine blades 有权
标题翻译：中心定位的切割齿在被覆盖的涡轮叶片上
公开(公告)号：US06890150B2
公开(公告)日：2005-05-10
申请号：US10638302
申请日：2003-08-12
申请人： Steven Eric Tomberg
发明人： Steven Eric Tomberg
IPC分类号： F01D11/08 , F01D5/14 , F01D5/20 , F02C7/28
CPC分类号： F01D5/141 , F01D5/225 , F05B2240/33 , F05D2240/30
摘要： A turbine bucket includes an airfoil having a tip shroud, a shank and an entry dovetail; a tip shroud seal projecting radially outwardly from the tip shroud and extending continuously between end edges of the tip shroud in a direction of rotation of the airfoil about a turbine axis; a cutter tooth carried by the tip shroud seal for enlarging a groove in an opposing fixed shroud, the cutter tooth having a center point located with reference to X, Y and Z axes, where the X-axis extends axially in an exhaust flow direction; the Y-axis extends in a direction of rotation of the turbine bucket; and the Z-axis extends radially through the intersection of the X and Y axes; wherein the center point is located about ½ inch along the Y-axis from the X=0 position, and wherein the Z-axis is located 0.517 inches from an outside edge of a seal pin extending along said entry dovetail, as measured in a direction normal to the shank of the bucket.
摘要翻译：涡轮机桶包括具有尖端罩，柄和入口燕尾榫的翼型件; 尖端护罩密封件，其从尖端护罩径向向外突出，并且沿着翼型件围绕涡轮机轴线的旋转方向在尖端护罩的端部边缘之间连续延伸; 由尖端护罩密封件承载的刀齿，用于扩大相对的固定护罩中的槽，刀齿具有相对于X，Y和Z轴定位的中心点，X轴在排气流动方向上轴向延伸; Y轴沿涡轮机的转动方向延伸; Z轴径向延伸穿过X轴和Y轴的交点; 其中所述中心点沿着所述X = 0位置的Y轴位于约1/2英寸处，并且其中所述Z轴位于距所述入口燕尾尾延伸的密封销的外边缘0.517英寸处，正常到桶的柄。

3. 发明授权

US06857853B1 Conical tip shroud fillet for a turbine bucket 有权
标题翻译：涡轮桶锥形尖端护罩圆角
公开(公告)号：US06857853B1
公开(公告)日：2005-02-22
申请号：US10639473
申请日：2003-08-13
申请人： Steven Eric Tomberg , Marvin Luther Neeley
发明人： Steven Eric Tomberg , Marvin Luther Neeley
IPC分类号： F01D11/08 , F01D5/14 , F01D5/16 , F01D5/22
CPC分类号： F01D5/225 , F01D5/147 , F05D2250/14 , F05D2250/16 , F05D2250/17 , F05D2250/70 , F05D2260/94 , Y02T50/673 , Y10S415/914
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 Dl is a distance between an intermediate point along a chord between edge points determined by offsets O2 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。作为每个X，Y位置处的形状参数比值的函数，圆角形状可以是抛物线形，椭圆形或双曲形，其中D1是沿着由偏移量O2和O2确定的边缘点之间的弦之间的中间点之间的距离，以及圆角表面上的肩点和D2是在翼尖和尖端护罩的交点处的肩点和顶点位置之间的距离。

4. 发明授权

US06808368B1 Airfoil shape for a turbine bucket 失效
标题翻译：涡轮叶片的翼型
公开(公告)号：US06808368B1
公开(公告)日：2004-10-26
申请号：US10460205
申请日：2003-06-13
申请人： Steven Eric Tomberg , David Samuel Pesetsky
发明人： Steven Eric Tomberg , David Samuel Pesetsky
IPC分类号： F01D514
CPC分类号： F01D5/141 , F01D5/14 , Y10S416/02
摘要： Second stage turbine buckets have airfoil profiles substantially in accordance with Cartesian coordinate values of X, Y and Z set forth Table 1 wherein X and Y values are in inches and the Z values are non-dimensional values from 0.088 to 0.92 convertible to Z distances in inches by multiplying the Z values by the height of the airfoil in inches. The X and Y values are distances which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete airfoil shape. The X and Y distances may be scalable as a function of the same constant or number to provide a scaled up or scaled down airfoil section for the bucket. The nominal airfoil given by the X, Y and Z distances lies within an envelop of ±0.160 inches in directions normal to the surface of the airfoil.
摘要翻译：第二级涡轮机叶片具有基本上符合X，Y和Z的笛卡尔坐标值的翼型，其中X，Y和Z表示在表1中，其中X和Y值是英寸，Z值是从0.088到0.92可转换成Z距离的无量纲值将Z值乘以翼型件的高度（英寸）。 X和Y值是通过平滑连续弧连接时定义每个距离Z处的翼型轮廓部分的距离。每个距离Z处的轮廓部分彼此平滑地连接以形成完整的翼型形状。作为相同常数或数字的函数，X和Y距离可以是可缩放的，以提供用于铲斗的放大或缩小的翼型部分。由X，Y和Z距离给出的额定翼型在垂直于翼面表面的方向上在±0.160英寸的范围内。

5. 发明授权

US07396211B2 Stator blade airfoil profile for a compressor 失效
标题翻译：用于压缩机的定子叶片翼型
公开(公告)号：US07396211B2
公开(公告)日：2008-07-08
申请号：US11392514
申请日：2006-03-30
申请人： Steven Eric Tomberg , Venkata Siva Chaluvadi
发明人： Steven Eric Tomberg , Venkata Siva Chaluvadi
IPC分类号： B64C27/46
CPC分类号： F01D5/141 , F04D29/544 , Y10S416/02 , Y10S416/05
摘要： Eleventh stage stator vanes for a compressor comprise airfoil profiles substantially in accordance with Cartesian coordinate values of x, Y and Z set forth in inches in Table I, wherein the Z coordinate values are perpendicular distances from planes normal to a radius from the compressor centerline and containing the X and Y values with the Z value commencing at zero in the X, Y plane at a radial aerodynamic section of the airfoil. X and Y are coordinate values defining the airfoil profile at each distance Z. The X, Y and Z values may be scaled to provide a scaled-up or scaled-down airfoil section for each stator vane.
摘要翻译：用于压缩机的第十一级定子叶片包括基本上按照表I中以英寸为单位的x，Y和Z的笛卡尔坐标值的翼型，其中Z坐标值是垂直于来自压缩机中心线的半径的平面的垂直距离，以及包含在翼型的径向空气动力学部分处的X，Y平面中从零开始的Z值的X和Y值。 X和Y是在每个距离Z处定义翼型轮廓的坐标值.X，Y和Z值可以被缩放以为每个定子叶片提供放大或缩小的翼型部分。

6. 发明授权

US06851931B1 Turbine bucket tip shroud edge profile 有权
标题翻译：涡轮斗尖护罩边缘型材
公开(公告)号：US06851931B1
公开(公告)日：2005-02-08
申请号：US10639459
申请日：2003-08-13
申请人： Steven Eric Tomberg
发明人： Steven Eric Tomberg
IPC分类号： F01D11/08 , F01D5/14 , F01D5/16 , F01D5/22
CPC分类号： F01D5/225 , F01D5/141 , F01D5/143 , F01D5/147 , 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 1-7 and 8-15, respectively, set forth in Table I. The X and Y values are distances in inches which, when respective points 1-7 and 8-15 are connected by smooth, continuing arcs, define the leading and trailing edge tip shroud profiles. An airfoil profile at 92% 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按照表I中所示的点1-7和8-15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，当相应点1-7和8-15通过光滑连续的弧连接时，可以定义前缘和后缘尖端护罩轮廓。 92％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。成型的前缘和后缘尖端护罩相对于翼型轮廓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。

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