某型发动机涡轮叶片断裂故障分析  

Fault Analysis of Certain Aero-Engine Turbine Blades Broken

作　　者：李武元 夏致斌[2] 付姮 涂昌青 

机构地区：[1]中航工业南方航空动力机械公司,株洲412002 [2]株洲职业技术学院,株洲412001

出　　处：《宇航材料工艺》2013年第5期81-87,共7页Aerospace Materials & Technology

摘　　要：某型航空发动机进行地面开车时涡轮叶片失效。通过对发动机的分解检查,断裂叶片的冶金分析,确定低压一级涡轮工作叶片为发动机故障的肇事件,其断裂性质为过载断裂;通过对低压一级涡轮工作叶片和导向叶片等零件间隙的计算分析,加工过程复查、疲劳试验及相关尺寸链计算,并采用故障树法对叶片断裂原因进行了系统分析,确定低压一级涡轮工作叶片断裂是其与低压一级涡轮导向叶片之间产生轴向碰磨引起的;该发动机在厂内试车时多次喘振引起一级导向器内机匣和定距半环局部变形,造成低压一级工作叶片与导向叶片在上缘板处的轴向间隙消失是轴向碰磨产生的原因。针对故障原因,制定了控制气动稳定性检查次数,控制各级涡轮工作叶片上下缘板端面轴向错移量,改进定距半环,控制定距半环与涡轮机匣安装槽轴向间隙,试车后检查低压涡轮后轴承外环跑道痕迹宽度等改进措施。The certain enging was disassembled and inspected because of its turbine blades being invalidated at ground starting. In this paper, it records the fault condition, takes computational analysis of clearance between low pressure first stage turbine working blades and low pressure first stage guide blades of the fault engine, takes metallur- gical analysis and workpiece processing analysis and durability testing and mutuality dimension chain computing for engine broken blades. Taking systems analysis for blades broken reason by fault tree, it finds out the reason of engine blades invalidated and advances improving adviees.

关 键 词：发动机 涡轮叶片 故障 轴向碰磨 

分 类 号：V261.31[航空宇航科学与技术—航空宇航制造工程]