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    Methods and apparatus for assembling gas turbine engines
    2.
    发明授权
    Methods and apparatus for assembling gas turbine engines 有权
    燃气轮机发动机组装方法及装置

    公开(公告)号：US07360990B2

    公开(公告)日：2008-04-22

    申请号：US10964303

    申请日：2004-10-13

    申请人： Roger Owen Barbe ,  Mitchell Jay Headley ,  Scott Howard Pelletier ,  David N. Rosenow

    发明人： Roger Owen Barbe ,  Mitchell Jay Headley ,  Scott Howard Pelletier ,  David N. Rosenow

    IPC分类号： F04D29/56

    CPC分类号： F01D17/162 ,  Y10S384/906

    摘要： A method enables a variable vane assembly for a gas turbine engine including a casing and an inner shroud to be assembled. The method comprises providing at least one variable vane including a radially inner spindle that has a substantially circular cross-sectional shape, and coupling the variable vane radially between the casing and the inner shroud such that the radially inner spindle is rotatably coupled within an opening extending through the inner shroud, wherein the opening has a non-circular cross-sectional profile.

    摘要翻译： 一种方法使得能够组装用于包括壳体和内护罩的燃气涡轮发动机的可变叶片组件。 该方法包括提供包括径向内心轴的至少一个可变叶片，其具有基本上圆形的横截面形状，并且将可变叶片径向地联接在壳体和内护罩之间，使得径向内心轴可旋转地联接在开口延伸 通过内护罩，其中开口具有非圆形横截面轮廓。

    IMPARTING DEEP COMPRESSIVE RESIDUAL STRESSES INTO A GAS TURBINE ENGINE AIRFOIL PERIPHERAL REPAIR WELDMENT
    4.
    发明申请
    IMPARTING DEEP COMPRESSIVE RESIDUAL STRESSES INTO A GAS TURBINE ENGINE AIRFOIL PERIPHERAL REPAIR WELDMENT 审中-公开
    将深层压缩残余应力引入气体涡轮发动机气翼外围修复维修

    公开(公告)号：US20090313823A1

    公开(公告)日：2009-12-24

    申请号：US12144940

    申请日：2008-06-24

    申请人： Todd Jay Rockstroh ,  Seetha Ramaiah Mannava ,  Roger Owen Barbe

    发明人： Todd Jay Rockstroh ,  Seetha Ramaiah Mannava ,  Roger Owen Barbe

    IPC分类号： B23P6/00

    CPC分类号： B23P9/02 ,  B23P6/007 ,  B23P9/04 ,  C21D7/06 ,  C21D9/0068 ,  C21D10/005 ,  C21D2221/00 ,  F01D5/005 ,  F01D5/286 ,  F05D2230/10 ,  F05D2230/232 ,  F05D2230/90 ,  Y02T50/672 ,  Y02T50/673 ,  Y10T29/49318

    摘要： A gas turbine engine airfoil is repaired by machining away airfoil material along at least a portion of at least one of leading and trailing edges and a radially outer tip forming at least one cut-back area and forming a weldment by welding successive beads of welding material into the cut-back area. Desired finished dimensions of the repaired airfoil are obtained by machining away some of the weld bead material in the weldment and then deep compressive residual stresses are imparted in a pre-stressed region extending into and encompassing the weldment and a portion of the airfoil adjacent the weldment. The compressive residual stresses may be are imparted after either rough machining or final finishing thereafter of the weldment. The cut-back area may extend up to about 90% of the airfoil's span and have a maximum cut-back depth up to about 0.22 inches.

    摘要翻译： 燃气涡轮发动机翼型件通过沿着前缘和后缘中的至少一个的至少一部分加工掉翼型材料和形成至少一个切割区域的径向外部尖端进行修复，并通过焊接连续的焊接材料珠形成焊件 进入切割区域。 修理的翼型件的期望成品尺寸通过机械加工焊接件中的一些焊缝材料而获得，然后在延伸到焊接件中并包围焊件的预应力区域中施加深度的压缩残余应力，并且靠近焊件的翼型件的一部分 。 可以在焊接后的粗加工或最终精加工之后赋予压缩残余应力。 切割区域可以延伸至翼型跨度的大约90％，并且具有最大约为0.22英寸的切割深度。

    Countering laser shock peening induced blade twist
    5.
    发明授权
    Countering laser shock peening induced blade twist 失效
    对抗激光冲击硬化诱发叶片扭转

    公开(公告)号：US07204677B2

    公开(公告)日：2007-04-17

    申请号：US11171087

    申请日：2005-06-30

    申请人： Seetha Ramaiah Mannava ,  Todd Jay Rockstroh ,  Roger Owen Barbe

    发明人： Seetha Ramaiah Mannava ,  Todd Jay Rockstroh ,  Roger Owen Barbe

    IPC分类号： F01D5/14

    CPC分类号： F01D5/286 ,  C21D7/06 ,  C21D10/005 ,  F01D5/141 ,  F01D5/3038 ,  F05D2230/41 ,  Y02T50/673

    摘要： A method for laser shock peening a gas turbine engine blade includes laser shock peening a thin airfoil of the blade, forming a laser shock induced twist in the airfoil, and altering a root of the blade to counter the laser shock induced twist in the airfoil. The altering may be done after the laser shock peening. The altering may be done before the laser shock peening during casting or forging of the blade or during a machining or broaching procedure which cuts a shape of the root. One embodiment of the altering includes forming the root with an altered root centerline having an altered centerline angle with respect to a predetermined root centerline designed for a non-laser shock peened airfoil of the blade.

    摘要翻译： 一种用于激光冲击喷丸机的燃气涡轮发动机叶片的方法包括激光冲击喷丸刀片的薄翼型，在翼型中形成激光冲击引起的扭曲，以及改变叶片的根部以抵抗机翼中的激光冲击引起的扭曲。 可以在激光冲击硬化后进行更换。 在刀片的铸造或锻造期间或在切割根部的形状的加工或拉削过程期间，可以在激光冲击锤击之前进行改变。 改变的一个实施例包括形成具有相对于为刀片的非激光冲击喷丸翼型设计的预定根中心线具有改变的中心线角的改变的根中心线的根部。

    Countering laser shock peening induced airfoil twist using shot peening
    6.
    发明授权
    Countering laser shock peening induced airfoil twist using shot peening 失效

    公开(公告)号：US07217102B2

    公开(公告)日：2007-05-15

    申请号：US11171147

    申请日：2005-06-30

    申请人： Todd Jay Rockstroh ,  Roger Owen Barbe ,  Seetha Ramaiah Mannava

    发明人： Todd Jay Rockstroh ,  Roger Owen Barbe ,  Seetha Ramaiah Mannava

    IPC分类号： F01D5/14

    CPC分类号： F01D5/286 ,  B24C1/10 ,  Y02T50/673 ,  Y10T29/4932

    摘要： A gas turbine engine blade is laser shock peened by laser shock peening a thin airfoil of the blade, forming a laser shock induced twist in the airfoil, and shot peening a portion of the airfoil to counter the laser shock induced twist in the airfoil. The shot peening may be performed before or after the laser shock peening. The shot peening may be applied over a laser shock peened surface formed by the laser shock peening. The shot peening may be performed asymmetrically on asymmetrically shot peened pressure and suction side areas of pressure and suction sides, respectively, of the airfoil. A shot peened patch near a blade tip may be formed on one of pressure and suction sides of the airfoil wherein the airfoil extends radially outwardly from a blade platform to the blade tip of the blade.