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。

公开(公告)号：US07331755B2

公开(公告)日：2008-02-19

申请号：US10853609

申请日：2004-05-25

申请人： Thomas Froats Broderick ,  Ronald Lance Galley ,  Clifford Earl Shamblen ,  David Edwin Budinger ,  Reed Roy Oliver ,  Roger Owen Barbe

发明人： Thomas Froats Broderick ,  Ronald Lance Galley ,  Clifford Earl Shamblen ,  David Edwin Budinger ,  Reed Roy Oliver ,  Roger Owen Barbe

IPC分类号： F01D9/00 ,  B23P15/04

CPC分类号： F01D5/288 ,  F01D9/044 ,  Y10T29/49323

摘要： A method for assembling a vane sector for a gas turbine engine, the vane sector including an airfoil vane and a platform includes depositing a wear coating material onto a selected area of the platform, positioning the platform adjacent to the airfoil vane, and executing a brazing operation such that the airfoil vane is permanently coupled to the platform portion and such that the wear coating material is bonded across a predefined area of the platform.

摘要翻译： 一种用于组装用于燃气涡轮发动机的叶片扇区的方法，包括翼型叶片和平台的叶片扇区包括将耐磨涂层材料沉积到平台的选定区域上，将平台定位成邻近翼型叶片，并执行钎焊 操作使得翼型叶片永久地联接到平台部分，并且使得磨损涂层材料跨越平台的预定区域结合。

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.

公开(公告)号：US06550254B2

公开(公告)日：2003-04-22

申请号：US09932585

申请日：2001-08-17

申请人： Robert Proctor ,  Julius John Montgomery ,  Michael Jay Epstein ,  Roger Owen Barbe ,  Hai Buu Sam ,  James Bernar Ogzewalla ,  Andrew David Kemp ,  Bryan Keith Doloresco

发明人： Robert Proctor ,  Julius John Montgomery ,  Michael Jay Epstein ,  Roger Owen Barbe ,  Hai Buu Sam ,  James Bernar Ogzewalla ,  Andrew David Kemp ,  Bryan Keith Doloresco

IPC分类号： F02C608

CPC分类号： F01D9/041 ,  F01D17/105 ,  F02C6/08 ,  F04D29/542

摘要： A gas turbine engine includes a compressor including a casing and a stator assembly. The casing extends around the stator assembly, the stator assembly including a plurality of stator vanes, and a plurality of bleed scoops. Adjacent stator vanes define a static high-pressure region, the bleed scoops formed at least partially within the high pressure region.

摘要翻译： 燃气涡轮发动机包括具有壳体和定子组件的压缩机。 壳体围绕定子组件延伸，定子组件包括多个定子叶片和多个排出勺。 邻近的定子叶片限定静态高压区域，至少部分地形成在高压区域内的排放勺。

公开(公告)号：US20110052406A1

公开(公告)日：2011-03-03

申请号：US12547066

申请日：2009-08-25

申请人： Robert William Bruce ,  Aaron Dennis Gastrich ,  John William Hanify ,  Roger Owen Barbe

发明人： Robert William Bruce ,  Aaron Dennis Gastrich ,  John William Hanify ,  Roger Owen Barbe

IPC分类号： F01D5/28 ,  C23C16/44

CPC分类号： F01D5/28 ,  C23C16/44 ,  F01D5/288 ,  F04D29/023 ,  F04D29/324 ,  F05D2230/313 ,  F05D2240/121 ,  F05D2240/303 ,  F05D2300/228 ,  F05D2300/611 ,  Y02T50/671 ,  Y02T50/673

摘要： A process for depositing coatings, and particularly erosion-resistant coatings suitable for protecting surfaces subjected to collisions with particles, such as a compressor blade of a gas turbine engine. The blade has an airfoil comprising oppositely-disposed convex and concave surfaces, oppositely-disposed leading and trailing edges defining therebetween a chord length of the airfoil, and a blade tip. An erosion-resistant coating is present on at least the concave surface, but not on the convex surface within at least 20% of the chord length from the leading edge.

摘要翻译： 一种用于沉积涂层的方法，特别是耐腐蚀涂层，适用于保护与颗粒碰撞的表面，例如燃气涡轮发动机的压缩机叶片。 叶片具有包括相对设置的凸形和凹形表面的翼型件，相对设置的前缘和后缘在其间限定翼型的翼弦长度和叶片尖端。 至少在凹形表面上存在防侵蚀涂层，而不存在于来自前缘的至少20％的弦长中的凸表面上。

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。

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。