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。