公开(公告)号：US6033185A

公开(公告)日：2000-03-07

申请号：US161935

申请日：1998-09-28

申请人： Andrew J. Lammas ,  William T. Dingwell ,  Anthony E. Hungler

发明人： Andrew J. Lammas ,  William T. Dingwell ,  Anthony E. Hungler

IPC分类号： F01D5/30

CPC分类号： F01D5/3038 ,  Y02T50/673

摘要： A rotor blade includes an airfoil, an integral platform, and a dovetail integrally joined to the platform. The dovetail includes a neck extending between a pair of dovetail lobes configured to engage a complementary slot in a rotor disk. The dovetail includes an undercut extending between an outer face of the dovetail lobes and the neck for introducing a stress concentration thereat. The stress concentration relieves stress at the outer face at the expense of the neck for increasing the high cycle fatigue life of the blade.

摘要翻译： 转子叶片包括一体地连接到平台的翼型件，整体式平台和燕尾榫。 燕尾榫包括在一对燕尾形突起之间延伸的颈部，其构造成接合转子盘中的互补槽。 燕尾包括在燕尾形叶片的外表面和颈部之间延伸的底切，用于在其上引入应力集中。 应力集中减轻了外表面的应力，牺牲了颈部的增加叶片的高循环疲劳寿命。

公开(公告)号：US06267558B1

公开(公告)日：2001-07-31

申请号：US09318641

申请日：1999-05-26

申请人： William T. Dingwell ,  Andrew J. Lammas ,  Herbert Halila

发明人： William T. Dingwell ,  Andrew J. Lammas ,  Herbert Halila

IPC分类号： B63H120

CPC分类号： F01D5/3007 ,  C21D7/06 ,  F01D5/286 ,  F01D5/3092

摘要： An article and a method for improving an article that results in a reduction or elimination of damage due to fretting from contact of similar metals. The invention specifically reduces wear-related fretting between titanium alloy parts by lowering the stresses between mating parts. An aluminum bronze coating is applied to one of the parts. The aluminum bronze coating provides an improvement over prior art coatings in reducing coefficient of friction between the parts. Additionally, the cumulative stresses at the surface of the parts is reduced by a dual intensity peening treatment. This involves a first peening operation using large peening media that provides a compressive stress to the required depth. This first peening operation is followed by a second peening operation that provides additional compressive stresses closer to the dovetail surface. The combined metallurgical and mechanical improvement results in a system with less susceptibility to fretting damage and corresponding improved fatigue resistance.

摘要翻译： 一种用于改善制品的制品和方法，其导致由于类似金属的接触而导致的微小损伤的减少或消除。 本发明通过降低配合部件之间的应力来具体地减少钛合金部件之间的磨损相关的微动。 将铝青铜涂层施加到其中一个部件。 铝青铜涂层在减少部件之间的摩擦系数方面提供了优于现有技术的涂层。 另外，通过双重强度喷丸处理减少了部件表面的累积应力。 这涉及使用提供压缩应力到所需深度的大型喷丸介质的第一次喷丸操作。 该第一喷丸操作之后是第二喷丸操作，其提供更靠近燕尾表面的附加压缩应力。 组合的冶金和机械改进导致系统对微动损坏的敏感性较小并且相应地改善的耐疲劳性。

公开(公告)号：US06250166B1

公开(公告)日：2001-06-26

申请号：US09327276

申请日：1999-06-04

申请人： William T. Dingwell ,  Andrew J. Lammas

发明人： William T. Dingwell ,  Andrew J. Lammas

IPC分类号： G01N302

CPC分类号： G01N3/32 ,  G01N2203/0246

摘要： A dovetail of a rotor blade is mounted in a complementary slot in a rotor disk. Life of the dovetail is simulated by providing a specimen dovetail mounted in a complementary slot in a fixture. Relative stiffness of the specimen dovetail and fixture are tailored to simulate the loading profile between the blade dovetail and rotor disk. Load is cycled between the specimen dovetail and fixture for determining life of the dovetail.

摘要翻译： 转子叶片的燕尾安装在转子盘的互补槽中。 通过提供安装在夹具中的互补槽中的样本燕尾榫来模拟燕尾榫的寿命。 试样燕尾和夹具的相对刚度被定制以模拟叶片燕尾榫和转子盘之间的载荷分布。 在样品燕尾榫和夹具之间循环加载，以确定燕尾榫的寿命。

公开(公告)号：US06551057B1

公开(公告)日：2003-04-22

申请号：US09444623

申请日：1999-11-22

申请人： Frederic G. Haaser ,  Wayne R. Bowen ,  William T. Dingwell ,  Michael Even-Nur ,  James C. Przytulski

发明人： Frederic G. Haaser ,  Wayne R. Bowen ,  William T. Dingwell ,  Michael Even-Nur ,  James C. Przytulski

IPC分类号： F01D2504

CPC分类号： F04D29/563 ,  F01D17/162 ,  F01D25/04 ,  F04D29/668 ,  F16C3/12 ,  F16C3/22 ,  F16C2360/23

摘要： A torque shaft assembly includes a hollow tube with a central axis disposed between and fixedly connected to first and second crankshafts at first and second distal ends, respectively, of the tube for movement of an array of connecting members such as push rods. A hollow interior of tube between the first and second crankshafts is filled with a sufficient quantity of flowable inertia material or damping media to absorb vibratory energy by friction during operation of the engine. The hollow interior is preferably filled with a quantity of damping media to a level by volume of about 98% and a preferred flowable inertia material is round steel shot. A plurality of spaced-apart clevises are fixedly attached to a tube wall on an outer surface of the tube wall surrounding the hollow interior. Each clevis includes connection means disposed away from the wall outer surface for connection with an actuator for movement of the array of adjustable devices such as variable stator vanes.

摘要翻译： 扭矩轴组件包括中空管，其中心轴分别设置在第一和第二曲轴的第一和第二远端处并分别固定地连接到第一和第二远端，并且固定地连接到用于使诸如推杆的连接构件的阵列的运动的管中。 在第一和第二曲轴之间的管的中空内部填充有足够量的可流动的惯性材料或阻尼介质，以通过在发动机运行期间的摩擦吸收振动能。 中空内部优选地填充有一定量的阻尼介质，体积达到约98％，优选的可流动的惯性材料是圆钢。 多个间隔开的夹头固定地附接到围绕中空内部的管壁的外表面上的管壁。 每个U形夹包括远离壁外表面设置的连接装置，用于与致动器连接，用于可调节装置阵列如可变定子叶片的移动。

公开(公告)号：US06532656B1

公开(公告)日：2003-03-18

申请号：US09974313

申请日：2001-10-10

申请人： Melvin H. Wilkins ,  Sean J. Corrigan ,  William T. Dingwell

发明人： Melvin H. Wilkins ,  Sean J. Corrigan ,  William T. Dingwell

IPC分类号： B23P1500

CPC分类号： B23P6/007 ,  B23K31/02 ,  B23K2101/001 ,  F01D5/005 ,  Y02T50/673 ,  Y10T29/49318 ,  Y10T29/49339 ,  Y10T29/49737 ,  Y10T29/49996

摘要： A method of repairing a gas turbine engine compressor blade airfoils includes machining away airfoil material along leading and trailing edges and a radially outer tip of the airfoil to form leading edge, trailing edge, and tip cut-backs. Then beads of welding material are welded onto the leading edge, trailing edge, and tip cut-backs. Then some of the weld material is machined away from the weld bead to obtain desired finished dimensions of the leading and trailing edges and radially outer tip. Blade material along only radially outermost portions of the leading and trailing edges extending from the tip towards a base of the airfoil is machined away. A rounded corner is formed between the leading edge and trailing edge cut-backs and unmachined portions of the airfoil between the outermost portions of the leading and trailing edges and the base of the airfoil.

摘要翻译： 修理燃气涡轮发动机压缩机叶片翼型件的方法包括沿着前缘和后缘以及翼型件的径向外端尖端去除机翼材料，以形成前缘，后缘和末端切口。 然后将焊接材料的焊料焊接到前缘，后缘和尖端切割。 然后将一些焊接材料加工成远离焊道，以获得前缘和后缘以及径向外端的所需最终尺寸。 沿着从尖端朝向翼型件的基部延伸的前缘和后缘的径向最外部的刀片材料被加工掉。 在前缘和后缘切割件之间形成圆角，并且在前缘和后缘的最外部分与翼型的基部之间形成翼型件的未加工部分。