航空发动机
航空髮動機
항공발동궤
AERO ENGINE
2012年
2期
55-58
,共4页
高压压气机%静子叶片%掉角故障%航空发动机
高壓壓氣機%靜子葉片%掉角故障%航空髮動機
고압압기궤%정자협편%도각고장%항공발동궤
HP Compressor: stator blade%blade fracture failure%acrnengine
针对某型发动机高压压气机第6级静子叶片掉角故障,分别进行了断口分析、强度计算、振动模态试验和整机动应力测试,综合分析结果表明：第6级静子叶片掉角断口均属于高周疲劳;实测第9阶振型的最大相对振动应力区与故障叶片的裂纹起始位置吻合;第9阶自振频率对叶尖附近的弦长、厚度及尾缘R的尺寸微小变化很敏感。采取了增加频率限制、对涂＂W＂漆前的吹砂工艺进行细化以保护叶片的措施,使得该故障得以排除。
針對某型髮動機高壓壓氣機第6級靜子葉片掉角故障,分彆進行瞭斷口分析、彊度計算、振動模態試驗和整機動應力測試,綜閤分析結果錶明：第6級靜子葉片掉角斷口均屬于高週疲勞;實測第9階振型的最大相對振動應力區與故障葉片的裂紋起始位置吻閤;第9階自振頻率對葉尖附近的絃長、厚度及尾緣R的呎吋微小變化很敏感。採取瞭增加頻率限製、對塗＂W＂漆前的吹砂工藝進行細化以保護葉片的措施,使得該故障得以排除。
침대모형발동궤고압압기궤제6급정자협편도각고장,분별진행료단구분석、강도계산、진동모태시험화정궤동응력측시,종합분석결과표명：제6급정자협편도각단구균속우고주피로;실측제9계진형적최대상대진동응력구여고장협편적렬문기시위치문합;제9계자진빈솔대협첨부근적현장、후도급미연R적척촌미소변화흔민감。채취료증가빈솔한제、대도＂W＂칠전적취사공예진행세화이보호협편적조시,사득해고장득이배제。
The fraeture analysis, strength calculation, vibration modal test and engine dynamic stress measurement were conducted for the sixth-stage high-pressure stator blade fracture failure of an aeroengine. The analysis results show thal the sixth-stage slator blade fracture failure is caused by high cycle fatigue. The measured biggest relative vibration stress region of the ninth mode is correspond with initial position of tailured blade crack. The nintil-slage natural frequency is very sensitive to the slight variations of chord length near tip, thickness and size of trailing edge R. The frequency restrict method and tile sand blasting technics refined before "w" painting are adopted to protect blade and eliminate failure.
