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1. 发明授权

US06474948B1 Third-stage turbine bucket airfoil 失效
标题翻译：第三级涡轮机叶翼
公开(公告)号：US06474948B1
公开(公告)日：2002-11-05
申请号：US09886406
申请日：2001-06-22
申请人： Peter Paul Pirolla , Gunnar Leif Siden , David John Humanchuk , Steven Robert Brassfield , Paul Stuart Wilson
发明人： Peter Paul Pirolla , Gunnar Leif Siden , David John Humanchuk , Steven Robert Brassfield , Paul Stuart Wilson
IPC分类号： F01D514
CPC分类号： F01D5/141 , F05D2240/301 , Y10S416/02 , Y10S416/05
摘要： The third-stage buckets have airfoil profiles substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in inches in Table I wherein Z is a perpendicular distance from a plane normal to a radius of the turbine centerline and containing the X and Y values with the Z value commencing at zero in the X, Y plane at the radially innermost aerodynamic section of the airfoil and X and Y are coordinates defining the airfoil profile at each distance Z. The X, Y and Z values may be scaled as a function of the same constant or number to provide a scaled-up or scaled-down airfoil section for the bucket.
摘要翻译：第三级铲斗具有基本上符合表I中以英寸表示的X，Y和Z的笛卡尔坐标值的翼型，其中Z是垂直于涡轮机中心线半径的平面的垂直距离，并且包含X和 Y值在Z轴的X，Y平面上在X轴和Y轴的径向最内空气动力学部分处开始为零，X和Y是在每个距离Z处定义翼型轮廓的坐标.X，Y和Z值可以被缩放为相同的常数或数字的功能来提供用于铲斗的放大或缩小的翼型部分。

2. 发明授权

US06503059B1 Fourth-stage turbine bucket airfoil 失效
标题翻译：第四级涡轮机桶翼型
公开(公告)号：US06503059B1
公开(公告)日：2003-01-07
申请号：US09899543
申请日：2001-07-06
申请人： Wilson Frost , Mark Edward Stegemiller , Andrew Charles Powis , Peter P. Pirolla , David John Humanchuk , Gunnar Leif Siden
发明人： Wilson Frost , Mark Edward Stegemiller , Andrew Charles Powis , Peter P. Pirolla , David John Humanchuk , Gunnar Leif Siden
IPC分类号： F01D514
CPC分类号： F01D5/141 , F05D2240/301 , Y10S416/02
摘要： The fourth-stage buckets have airfoil profiles substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in inches in Table I wherein Z is a perpendicular distance from a plane normal to a radius of the turbine centerline and containing the X and Y values with the Z value commencing at zero in the X, Y plane at the radially innermost aerodynamic section of the airfoil and X and Y are coordinate values defining the airfoil profile at each distance Z. The X, Y and Z values may be scaled as a function of the same constant or number to provide a scaled-up or scaled-down airfoil section for the bucket.
摘要翻译：第四级铲斗具有基本上符合表I中以英寸表示的X，Y和Z的笛卡尔坐标值的翼型，其中Z是垂直于涡轮机中心线半径的平面的垂直距离，并且包含X和 Y值在Z轴的X，Y平面上从零开始，X和Y在翼型的径向最内空气动力学部分处开始，X和Y是定义每个距离Z处的翼面轮廓的坐标值.X，Y和Z值可以被缩放作为相同常数或数字的函数，以提供用于铲斗的放大或缩小的翼型部分。

3. 发明授权

US08057169B2 Airfoil core shape for a turbine nozzle 有权
标题翻译：涡轮喷嘴的翼型形状
公开(公告)号：US08057169B2
公开(公告)日：2011-11-15
申请号：US12138580
申请日：2008-06-13
申请人： Edward Durell Benjamin, Jr. , David John Humanchuk , Daniel David Snook
发明人： Edward Durell Benjamin, Jr. , David John Humanchuk , Daniel David Snook
IPC分类号： F03B3/12
CPC分类号： F01D5/141 , F05D2220/3212 , F05D2250/74 , F05D2260/202
摘要： An article of manufacture includes an object having an airfoil core shape. The airfoil core shape has a nominal profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in TABLE 1 where 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 are joined smoothly with one another to form a complete airfoil core shape.
摘要翻译：制品包括具有翼型芯形状的物体。翼型芯形状具有基本上符合表1所示的X，Y和Z的笛卡尔坐标值的标称轮廓，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，每一个定义翼型轮廓部分距离Z以英寸为单位。在Z距离处的轮廓部分彼此平滑地连接以形成完整的翼型芯形状。

4. 发明授权

US07160078B2 Mechanical solution for rail retention of turbine nozzles 有权
标题翻译：涡轮喷嘴轨道保持的机械解决方案
公开(公告)号：US07160078B2
公开(公告)日：2007-01-09
申请号：US10947450
申请日：2004-09-23
申请人： Robert Walter Coign , David John Humanchuk , Leslie Tucker
发明人： Robert Walter Coign , David John Humanchuk , Leslie Tucker
IPC分类号： F01D21/00 , F01D9/04
CPC分类号： F01D21/045 , F01D9/041 , F01D25/246 , Y10T29/49323
摘要： A mechanical arrangement for protection against catastrophic nozzle failures includes a turbine nozzle segment including an inner platform rail, a turbine nozzle inner support ring in part in axial registration with the rail on one side, an inner retainer segment secured to the inner support ring and in part in axially spaced registration relative to the rail on an axial side of the rail opposite from the support ring, a first inclined conical surface on the inner retainer segment, and a second inclined conical surface on the inner platform rail of the turbine nozzle, the second inclined conical surface opposing the first inclined conical surface, so as to bind the inner platform rail to the turbine nozzle between the inner retainer segment and the inner support ring, resulting in a wedge lock that prevents the inner platform from being lost downstream into rotating hardware of the turbine.
摘要翻译：用于防止灾难性喷嘴故障的机械装置包括涡轮喷嘴段，其包括内平台轨道，部分与一侧的轨道轴向对齐的涡轮喷嘴内支撑环，固定到内支撑环的内保持器节段部分在与支撑环相对的轨道的轴向侧上相对于轨道轴向间隔的配准，内保持器节段上的第一倾斜锥形表面和在涡轮喷嘴的内平台轨道上的第二倾斜锥形表面，与第一倾斜锥形表面相对的第二倾斜锥形表面，以便将内平台轨道与内部保持器节段和内部支撑环之间的涡轮喷嘴结合，导致楔形锁定，其防止内部平台从下游转入旋转涡轮机的硬件。

5. 发明授权

US06994520B2 Internal core profile for a turbine nozzle airfoil 有权
标题翻译：涡轮喷嘴翼型的内芯型材
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。

6. 发明授权

US06685434B1 Second stage turbine bucket airfoil 失效
标题翻译：二级涡轮机叶翼
公开(公告)号：US06685434B1
公开(公告)日：2004-02-03
申请号：US10244562
申请日：2002-09-17
申请人： David John Humanchuk , Craig Allen Bielek , Robert Alan Brittingham , James Tyson Balkcum , Andrew Jones, Jr.
发明人： David John Humanchuk , Craig Allen Bielek , Robert Alan Brittingham , James Tyson Balkcum , Andrew Jones, Jr.
IPC分类号： F01D514
CPC分类号： F01D5/14 , F01D5/141 , F05D2220/3212 , F05D2240/301 , F05D2250/20 , F05D2250/70 , F05D2250/74 , Y10S416/02
摘要： The second stage buckets have airfoil profiles substantially in accordance with Cartesian coordinate values of X, Y and Z set forth Table I wherein X and Y values are in inches and the Z value is non-dimensional along the bucket centerline 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 bucket. The nominal airfoil given by the X, Y and Z distances lies within an envelop of ±0.160 inches.
摘要翻译：第二级铲斗具有基本上符合X，Y和Z的笛卡尔坐标值的机翼型材，其中X和Y和Z列在表I中，其中X和Y值是英寸，Z值是沿着与涡轮机半径一致的铲斗中心线的无量纲，通过将Z值乘以翼型的高度并将根半径与结果相加，可以转换为Z轴距离涡轮轴的英寸。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±0.160英寸的范围内。

7. 发明授权

US06558122B1 Second-stage turbine bucket airfoil 失效
标题翻译：二级涡轮机叶翼
公开(公告)号：US06558122B1
公开(公告)日：2003-05-06
申请号：US09987433
申请日：2001-11-14
申请人： Liming Xu , Majid Ahmadi , David John Humanchuk , Nicholas Moretto , Richard Edward Delehanty
发明人： Liming Xu , Majid Ahmadi , David John Humanchuk , Nicholas Moretto , Richard Edward Delehanty
IPC分类号： F01D514
CPC分类号： F01D5/141 , Y10S416/02
摘要： The second-stage buckets have airfoil profiles substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in inches in Table I wherein Z is a perpendicular distance from a plane normal to a radius of the turbine centerline and containing the X and Y values with the Z value commencing at zero in the X, Y plane at the radially innermost aerodynamic section of the airfoil and X and Y are coordinate values defining the airfoil profile at each distance Z. The X, Y and Z values may be scaled as a function of the same constant or number to provide a scaled-up or scaled-down airfoil section for the bucket.
摘要翻译：第二级铲斗具有基本上符合表I中以英寸表示的X，Y和Z的笛卡尔坐标值的翼型，其中Z是垂直于涡轮中心线半径的平面的垂直距离，并且包含X和 Y值在Z轴的X，Y平面上从零开始，X和Y在翼型的径向最内空气动力学部分处开始，X和Y是定义每个距离Z处的翼面轮廓的坐标值.X，Y和Z值可以被缩放作为相同常数或数字的函数，以提供用于铲斗的放大或缩小的翼型部分。

8. 发明申请

US20090324415A1 AIRFOIL CORE SHAPE FOR A TURBINE NOZZLE 有权
标题翻译：用于涡轮喷嘴的气翼芯形
公开(公告)号：US20090324415A1
公开(公告)日：2009-12-31
申请号：US12138580
申请日：2008-06-13
申请人： Edward Durell Benjamin, JR. , David John Humanchuk , Daniel David Snook
发明人： Edward Durell Benjamin, JR. , David John Humanchuk , Daniel David Snook
IPC分类号： F01D5/14
CPC分类号： F01D5/141 , F05D2220/3212 , F05D2250/74 , F05D2260/202
摘要： An article of manufacture includes an object having an airfoil core shape. The airfoil core shape has a nominal profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in TABLE 1 where 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 are joined smoothly with one another to form a complete airfoil core shape.
摘要翻译：制品包括具有翼型芯形状的物体。翼型芯形状具有基本上符合表1所示的X，Y和Z的笛卡尔坐标值的标称轮廓，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，每一个定义翼型轮廓部分距离Z以英寸为单位。在Z距离处的轮廓部分彼此平滑地连接以形成完整的翼型芯形状。

9. 发明授权

US07094026B2 System for sealing an inner retainer segment and support ring in a gas turbine and methods therefor 失效
标题翻译：用于密封燃气轮机内部保持器节段和支撑环的系统及其方法
公开(公告)号：US07094026B2
公开(公告)日：2006-08-22
申请号：US10834116
申请日：2004-04-29
申请人： Robert Walter Coign , David John Humanchuk , Gregory Thomas Foster , Kevin Lee Worley
发明人： Robert Walter Coign , David John Humanchuk , Gregory Thomas Foster , Kevin Lee Worley
IPC分类号： F01D9/04
CPC分类号： F01D9/023
摘要： Arcuate seal layers conforming with one another are disposed between inner retainer segments and inner rails of nozzle segments of a gas turbine. The layers are secured to the aft axial face of the segments and project radially outwardly to seal against the forward axial faces of the rails. The rear axial faces of the rails have chordal seals for sealing against the forward axial faces of the support rings. The seal layers have radial cuts misaligned with one another in an axial direction to preclude leakage flows through gaps formed by the cuts. Arcuate spacers are staggered circumferentially with the arcuate retainer segments whereby an intermediate pressure plenum is formed between the finger seals and chordal seals.
摘要翻译：弧形密封层彼此配合设置在燃气轮机的内部保持器节段和喷嘴段的内部轨道之间。这些层被固定到段的后轴向面并径向向外突出以密封抵靠轨道的前轴向面。轨道的后轴向面具有用于密封支撑环的前轴向面的弦状密封件。密封层具有在轴向方向上彼此不对准的径向切口，以排除通过切口形成的间隙的泄漏流动。弧形间隔件与弓形保持器节段周向交错，由此在手指密封件和弦密封件之间形成中间压力室。

10. 发明授权

US06722853B1 Airfoil shape for a turbine nozzle 有权
标题翻译：涡轮喷嘴的翼型
公开(公告)号：US06722853B1
公开(公告)日：2004-04-20
申请号：US10301724
申请日：2002-11-22
申请人： David John Humanchuk , Matthew Troy Hafner , James B. Fehlberg
发明人： David John Humanchuk , Matthew Troy Hafner , James B. Fehlberg
IPC分类号： F01D514
CPC分类号： F01D5/141 , F05D2250/20 , F05D2250/70 , Y10S416/02
摘要： The second stage nozzle has an airfoil profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I wherein X and Y values are in inches and define airfoil profile sections at each distance Z and Z is a non-dimensional value from 0 to 1 convertible to Z distances in inches by multiplying the Z values of Table I by a height of the airfoil in inches. The profile sections at the Z distances are joined smoothly with one another to form a complete airfoil shape. The X and Y distances may be scalable to provide a scaled-up or scaled-down airfoil for the nozzle. The nominal airfoil given by the X, Y and Z distances lies within an envelope of ±0.100 inches.
摘要翻译：第二级喷嘴具有基本上根据表I所示的X，Y和Z的笛卡尔坐标值的翼型轮廓，其中X和Y值以英寸为单位，并且在每个距离Z处定义翼型轮廓部分，Z是无量纲从0到1的值可以通过将表I的Z值乘以翼型的高度（英寸）来以英寸换算为Z距离。 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。 X和Y距离可以是可缩放的，以为喷嘴提供放大或缩小的翼型。由X，Y和Z距离给出的额定翼型在±0.100英寸的范围内。

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