公开(公告)号：US06736599B1

公开(公告)日：2004-05-18

申请号：US10249870

申请日：2003-05-14

申请人： Curtis John Jacks ,  Craig Allen Bielek ,  Robert Walter Coign ,  Randall Gill

发明人： Curtis John Jacks ,  Craig Allen Bielek ,  Robert Walter Coign ,  Randall Gill

IPC分类号： F01D904

CPC分类号： F01D9/02 ,  F01D5/141 ,  F05D2200/10 ,  F05D2240/128 ,  F05D2240/301 ,  F05D2250/70

摘要： The first stage nozzles have airfoil profiles substantially in accordance with Cartesian coordinate values of X, Y and Z set forth Table 1. The X and Y values are in inches and the Z value is non-dimensional along the nozzle-stacking axis coincident with a turbine radius and convertible to a Z distance in inches from the turbine axis by multiplying the Z value by the height of the airfoil and adding the root radius to the result. 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 nozzle. The nominal airfoil given by the X, Y and Z distances lies within an envelope of ±0.160 inches.

摘要翻译： 第一级喷嘴具有基本上符合表1所示的X，Y和Z的笛卡尔坐标值的翼型轮廓.X和Y值以英寸为单位，并且Z值沿着与a的一致的喷嘴 - 堆叠轴线是无量纲的 涡轮机半径，并通过将Z值乘以翼型的高度并将根半径添加到结果中，将其与涡轮机轴的英寸距离Z转换成Z距离。 X和Y距离可以是可缩放的，作为相同常数或数字的函数，以提供用于喷嘴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±0.160英寸的范围内。

公开(公告)号：US07121787B2

公开(公告)日：2006-10-17

申请号：US10834055

申请日：2004-04-29

申请人： Curtis John Jacks ,  Robert Walter Coign ,  Randall Douglas Gill

发明人： Curtis John Jacks ,  Robert Walter Coign ,  Randall Douglas Gill

IPC分类号： F01D9/02 ,  F01D5/18

CPC分类号： F01D5/186 ,  F01D5/187 ,  F05D2240/81 ,  F05D2260/201 ,  F05D2260/2212 ,  F05D2260/22141

摘要： The trailing edge region of a nozzle airfoil is provided with a cooling configuration wherein post-impingement cooling air flows between radially spaced ribs defining convective cooling channels into a generally radially extending plenum. Cooling air in the plenum is split between film cooling holes for film cooling the pressure side of the trailing edge region and for flow about downstream pins for pin cooling the downstream regions of the opposite sides of the airfoil. The cooling air exiting the pins is directed through convective channels defined by a second set of radially spaced ribs and through exit apertures on the pressure side of the trailing edge.

摘要翻译： 喷嘴翼型件的后缘区域设置有冷却构造，其中后冲击冷却空气在限定对流冷却通道的径向隔开的肋之间流动到通常径向延伸的气室中。 气室中的冷却空气在膜冷却孔之间分开，用于薄膜冷却后缘区域的压力侧，并且用于在下游管脚处流动，用于针对冷却翼型相对侧的下游区域。 离开销的冷却空气被引导通过由第二组径向隔开的肋限定的对流通道，并通过后缘的压力侧上的出口孔。

公开(公告)号：US20050244264A1

公开(公告)日：2005-11-03

申请号：US10834055

申请日：2004-04-29

申请人： Curtis John Jacks ,  Robert Coign ,  Randall Gill

发明人： Curtis John Jacks ,  Robert Coign ,  Randall Gill

IPC分类号： F01D5/14 ,  F01D5/18

CPC分类号： F01D5/186 ,  F01D5/187 ,  F05D2240/81 ,  F05D2260/201 ,  F05D2260/2212 ,  F05D2260/22141

摘要： The trailing edge region of a nozzle airfoil is provided with a cooling configuration wherein post-impingement cooling air flows between radially spaced ribs defining convective cooling channels into a generally radially extending plenum. Cooling air in the plenum is split between film cooling holes for film cooling the pressure side of the trailing edge region and for flow about downstream pins for pin cooling the downstream regions of the opposite sides of the airfoil. The cooling air exiting the pins is directed through convective channels defined by a second set of radially spaced ribs and through exit apertures on the pressure side of the trailing edge.

摘要翻译： 喷嘴翼型件的后缘区域设置有冷却构造，其中后冲击冷却空气在限定对流冷却通道的径向隔开的肋之间流动到通常径向延伸的气室中。 气室中的冷却空气在膜冷却孔之间分开，用于薄膜冷却后缘区域的压力侧，并且用于在下游管脚处流动，用于针对冷却翼型相对侧的下游区域。 离开销的冷却空气被引导通过由第二组径向隔开的肋限定的对流通道，并通过后缘的压力侧上的出口孔。

公开(公告)号：US06994520B2

公开(公告)日：2006-02-07

申请号：US10853240

申请日：2004-05-26

申请人： David John Humanchuk ,  Curtis John Jacks ,  Robert W. Coign

发明人： David John Humanchuk ,  Curtis John Jacks ,  Robert W. Coign

IPC分类号： F01D9/06

CPC分类号： F01D5/141 ,  B22C9/10 ,  F01D5/18 ,  F05D2230/21 ,  F05D2230/211

摘要： First stage nozzle airfoils have internal core profiles substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I wherein X, Y and Z values are in inches. The X and Y values are distances which, when connected by smooth continuing arcs, define internal core profile sections at each radial distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete internal core profile. The X, Y and Z distances may be scalable as a function of the same constant or number to provide a scaled-up or scaled-down internal core profile. The nominal internal core profile given by the X, Y and Z distances lies within an envelope of ±0.030 inches in directions normal to any internal core surface location.

摘要翻译： 第一级喷嘴翼型件具有基本上根据表I中列出的X，Y和Z的笛卡尔坐标值的内部芯轮廓，其中X，Y和Z值为英寸。 X和Y值是当通过光滑连续的弧连接时在每个径向距离Z处限定内部芯轮廓部分的距离。每个距离Z处的轮廓部分彼此平滑地连接以形成完整的内部芯轮廓。 X，Y和Z距离可以是可扩展的，作为相同常数或数字的函数，以提供按比例放大或缩小的内核配置文件。 由X，Y和Z距离给出的标称内部芯轮廓在垂直于任何内部芯部表面位置的方向上在±0.030英寸的包络内。

公开(公告)号：US07140832B2

公开(公告)日：2006-11-28

申请号：US10907504

申请日：2005-04-04

申请人： Curtis John Jacks

发明人： Curtis John Jacks

IPC分类号： F01D17/00

CPC分类号： F01D9/041 ,  F01D25/12 ,  F01D25/36 ,  F05D2240/128 ,  F05D2250/411 ,  F05D2260/80 ,  F05D2270/11 ,  F05D2270/112

摘要： A method for distributing effects of a circumferential hot streak condition in a turbine includes communicating a control signal to a rotator moving a stator ring with the rotator in response to the control signal.

摘要翻译： 用于分配涡轮机中周向热条纹状态的影响的方法包括：响应于控制信号，将控制信号传递到与转子一起移动定子环的转子。