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    Nozzle blade airfoil profile for a turbine
    1.
    发明申请
    Nozzle blade airfoil profile for a turbine 有权
    用于涡轮机的喷嘴叶片翼型

    公开(公告)号：US20070177981A1

    公开(公告)日：2007-08-02

    申请号：US11340577

    申请日：2006-01-27

    申请人： Thomas Vandeputte ,  John Greene ,  Peter Selent ,  Linda Farral ,  Sze Bun Chan ,  Brian Arness

    发明人： Thomas Vandeputte ,  John Greene ,  Peter Selent ,  Linda Farral ,  Sze Bun Chan ,  Brian Arness

    IPC分类号： B64C27/46

    CPC分类号： F01D5/141 ,  F05D2240/128 ,  F05D2250/74 ,  Y10S416/02

    摘要： First stage stator vanes for a turbine comprised airfoil profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in inches in Table I, which define a plurality of radially spaced profile sections forming the nominal profile. The Z coordinate values for each profile section are radial distances from the turbine axis to a portion of the surface of revolution about the axis containing the profile section. The X and Y values for each profile section are coordinate values which, when connected by smooth continuing arcs define the airfoil profile section along the surface of revolution portion. The radially spaced profile sections are joined smoothly with one another to form the nominal airfoil profile.

    摘要翻译： 用于涡轮机的第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分布，其定义了形成标称轮廓的多个径向间隔的轮廓部分。 每个轮廓截面的Z坐标值是从涡轮机轴线到围绕围绕轮廓部分的轴线的旋转表面的一部分的径向距离。 每个轮廓截面的X和Y值是坐标值，当通过平滑的连续弧连接时，沿着旋转部分的表面限定翼型轮廓部分。 径向隔开的轮廓部分彼此平滑地连接以形成标称翼型轮廓。

    Apparatus and methods for removing and installing a selected nozzle segment of a gas turbine in an axial direction
    2.
    发明申请
    Apparatus and methods for removing and installing a selected nozzle segment of a gas turbine in an axial direction 有权
    用于沿轴向移除和安装燃气涡轮机的选定喷嘴段的装置和方法

    公开(公告)号：US20050111969A1

    公开(公告)日：2005-05-26

    申请号：US10716449

    申请日：2003-11-20

    申请人： Brian Arness ,  John Greene ,  Linda Farral ,  Sze Bun Chan

    发明人： Brian Arness ,  John Greene ,  Linda Farral ,  Sze Bun Chan

    IPC分类号： F01D9/04 ,  F01D25/24 ,  F01D1/02

    CPC分类号： F01D9/042 ,  F01D25/246 ,  F05D2230/64 ,  F05D2230/80

    摘要： Nozzle segments are secured to a retention ring against circumferential rotation by anti-rotation pins extending generally axially between the outer bands of the nozzle segments and the retention ring. Retention plate segments overlie the ends of the pins, preventing axial removal thereof. To remove a selected nozzle segment, inner diameter retention plate segments and selected retention plate segments are removed, the latter exposing the ends of the pins for axial withdrawal. Upon removal of a predetermined number of pins, the nozzle segments adjacent the selected segment are displaced away from the latter segment to open a gap between the selected segment and adjacent segments whereby the selected segment can be removed in an axial direction.

    摘要翻译： 喷嘴段通过在喷嘴段的外带和保持环之间大致轴向延伸的防旋转销固定到保持环以防止圆周旋转。 保持板段覆盖销的端部，防止其轴向移除。 为了去除所选择的喷嘴段，去除内径保持板段和选定的保持板段，后者将引脚的端部暴露以用于轴向退出。 在移除预定数量的销之后，与所选择的段相邻的喷嘴段从后段移开，以打开选定段和相邻段之间的间隙，从而可以沿轴向移除所选段。

    Method and apparatus for assembling turbine nozzle assembly
    3.
    发明申请
    Method and apparatus for assembling turbine nozzle assembly 有权
    用于组装涡轮喷嘴组件的方法和装置

    公开(公告)号：US20070154305A1

    公开(公告)日：2007-07-05

    申请号：US11325185

    申请日：2006-01-04

    申请人： Brian Arness ,  John Greene ,  Sze Chan

    发明人： Brian Arness ,  John Greene ,  Sze Chan

    IPC分类号： F01D9/00

    CPC分类号： F01D9/041 ,  F01D11/005 ,  F01D25/246 ,  F05D2220/3212 ,  F05D2230/64 ,  F05D2240/57 ,  F05D2250/182 ,  F05D2260/30 ,  F05D2300/505

    摘要： A method for assembling a turbine nozzle assembly with respect to a combustor of a gas turbine engine is provided. The method includes coupling a radial outer retaining ring to an aft end of the combustor. A plurality of turbine nozzles is provided. Each turbine nozzle includes an inner band, a radially opposing outer band, and at least one vane extending between the inner band and the outer band. The outer band of each turbine nozzle is coupled to the outer retaining ring to define the turbine nozzle assembly. An inner retaining ring is positioned about an axis of the gas turbine engine and coupled to the inner band of each turbine nozzle.

    摘要翻译： 提供了一种用于组装相对于燃气涡轮发动机的燃烧器的涡轮喷嘴组件的方法。 该方法包括将径向外保持环联接到燃烧器的后端。 提供多个涡轮喷嘴。 每个涡轮喷嘴包括内带，径向相对的外带，以及在内带和外带之间延伸的至少一个叶片。 每个涡轮喷嘴的外带连接到外保持环以限定涡轮喷嘴组件。 内部保持环围绕燃气涡轮发动机的轴线定位并且联接到每个涡轮喷嘴的内部带。

    Pattern for the surface of a turbine shroud
    4.
    发明申请
    Pattern for the surface of a turbine shroud 有权

    公开(公告)号：US20060110248A1

    公开(公告)日：2006-05-25

    申请号：US10996878

    申请日：2004-11-24

    申请人： Warren Nelson ,  Brian Arness ,  Paul Marks ,  Raymond Chupp ,  Tara McGovern

    发明人： Warren Nelson ,  Brian Arness ,  Paul Marks ,  Raymond Chupp ,  Tara McGovern

    IPC分类号： F01D5/20

    CPC分类号： F01D11/12 ,  F01D11/122

    摘要： A pattern for improving aerodynamic performance of a turbine includes a material disposed in a pattern at a base surface of a turbine shroud such that the material is capable of abradable contact with a tip portion of a turbine bucket. The pattern includes a first plurality of ridges disposed at the base surface such that a first portion of the first plurality of ridges corresponding to a back portion of the turbine bucket is oriented at a first angle with respect to an axis of rotation of the turbine bucket. Each ridge of the first plurality of ridges has a first sidewall and a second sidewall having a first end and a second end. The first ends of the first and second sidewalls extend from the base surface. The first and second sidewalls slope toward each other with substantially equal but opposite slopes until meeting at the second ends of respective first and second sidewalls defining a centerline and a top portion of the ridge.

    AIRFOIL SHAPE FOR A TURBINE NOZZLE
    5.
    发明申请
    AIRFOIL SHAPE FOR A TURBINE NOZZLE 有权
    涡轮喷嘴气翼形状

    公开(公告)号：US20050025618A1

    公开(公告)日：2005-02-03

    申请号：US10630750

    申请日：2003-07-31

    申请人： Brian Arness ,  Robert By ,  Gunnar Siden ,  Poornathresan Krishnakumar ,  Bruce Smith ,  Peter Selent

    发明人： Brian Arness ,  Robert By ,  Gunnar Siden ,  Poornathresan Krishnakumar ,  Bruce Smith ,  Peter Selent

    IPC分类号： F01D9/02 ,  F01D5/14 ,  F01D1/02

    CPC分类号： F01D5/142 ,  F01D5/141

    摘要： The third 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 are non-dimensional values within a range from 0.1 to 0.9 convertible to Z distances in inches by multiplying the Z values of Table I within said range by a height of the airfoil in inches. The profile sections at the Z distances are joined smoothly with one another to form the nozzle 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 ±0.160 inches.

    摘要翻译： 第三级喷嘴具有基本上根据表I中列出的X，Y和Z的笛卡尔坐标值的翼型分布，其中X和Y值以英寸为单位，并且在每个距离Z和Z是非尺寸值，限定翼型剖面部分 在0.1至0.9的范围内，通过将表I的Z值乘以所述范围内的翼型高度（英寸），以英寸计算Z距离。 在Z距离处的轮廓部分彼此平滑地连接以形成喷嘴翼型形状。 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±0.160英寸的范围内。

    PATTERN FOR THE SURFACE OF A TURBINE SHROUD
    9.
    发明申请
    PATTERN FOR THE SURFACE OF A TURBINE SHROUD 有权
    涡轮机表面图案

    公开(公告)号：US20060110247A1

    公开(公告)日：2006-05-25

    申请号：US10907972

    申请日：2005-04-22

    申请人： Warren Nelson ,  Brian Arness ,  Paul Marks ,  Raymond Chupp ,  Tara McGovern

    发明人： Warren Nelson ,  Brian Arness ,  Paul Marks ,  Raymond Chupp ,  Tara McGovern

    IPC分类号： F01D5/20

    CPC分类号： F01D11/12 ,  F01D11/122

    摘要： An article of manufacture pattern for improving aerodynamic performance of a turbine including an abradable material capable of abradable contact. The abradable material is disposed in a pattern. The pattern includes a first plurality of ridges disposed at a base surface of the turbine. Each ridge of the first plurality of ridges has a first sidewall and a second sidewall having a first end and a second end. The first ends of the first and second sidewalls extend from the base surface. The first and second sidewalls slope toward each other with substantially equal but opposite slopes until meeting at the second ends of respective first and second sidewalls defining a centerline and a top portion of the ridge.

    摘要翻译： 一种用于改善涡轮机的空气动力性能的制造模式的制品，其包括能够耐磨的接触的耐磨材料。 耐磨材料以图案设置。 该图案包括设置在涡轮机的基面处的第一多个脊。 第一多个脊中的每个脊具有第一侧壁和具有第一端和第二端的第二侧壁。 第一和第二侧壁的第一端从基面延伸。 第一和第二侧壁彼此相对倾斜，具有基本上相等但相反的斜面，直到在相应的第一和第二侧壁的第二端处共同限定脊的中心线和顶部。