晶轴偏转对DD6带冠叶片频率特性的影响
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摘要
针对DD6单晶带冠叶片铸造过程中极易产生晶轴偏转,进而对叶片固有频率和相邻叶片叶冠间挤压力产生较大影响这一问题,采用有限元分析方法,对DD6单晶带冠叶片进行静应力和模态分析,获得了不同偏转角下叶片固有频率及叶冠间挤压力的变化规律。即随着偏转角β的增大,1、2阶固有频率升高,3、4阶固有频率非单调变化;同时,还将导致叶冠间挤压力减小,进一步影响固有频率。通过锤击法对该叶片频率进行了试验测量,对有限元分析的结果进行了验证。
When DD6 single crystal shrouded blade was produced by casting, crystal axis deflection which had a significant effect on the blade inherent frequency and the extrusion force of adjacent shroud can easi-ly occur. Static stress and mode analysis of DD6 single crystal shrounded blade was carried out by finite ele-ment method(FEM), and the change rule of blade inherent frequency and the extrusion force under differentcrystal axis deflection was found out. As the deflection angle β increased, the inherent frequency of thefirst two orders increased and the 3 rd, 4 th orders non-monotonically changed, which also lead to the decrease of the extrusion force and further affected the inherent frequency. An aero-engine blade frequencywas measured by the hammering method and finite element analysis results were verified.
When DD6 single crystal shrouded blade was produced by casting, crystal axis deflection which had a significant effect on the blade inherent frequency and the extrusion force of adjacent shroud can easi-ly occur. Static stress and mode analysis of DD6 single crystal shrounded blade was carried out by finite ele-ment method(FEM), and the change rule of blade inherent frequency and the extrusion force under differentcrystal axis deflection was found out. As the deflection angle β increased, the inherent frequency of thefirst two orders increased and the 3 rd, 4 th orders non-monotonically changed, which also lead to the decrease of the extrusion force and further affected the inherent frequency. An aero-engine blade frequencywas measured by the hammering method and finite element analysis results were verified.
引文
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[2]岳珠峰,吕震宙,杨治国,等.晶体取向的偏差和随机性对镍基单晶叶片强度与蠕变寿命的影响[J].航空动力学报,2003,18(4):477—480.
[3]高靖云,方磊,张成成,等.单晶涡轮叶片三维晶体取向相关性能分析及优化[J].航空动力学报,2016,31(2):289—298.
[4]岳珠峰,尹泽勇,杨治国.晶体取向对航空发动机单晶叶片结构强度和蠕变寿命的影响[J].航空发动机,1997,22(3):32—34.
[5]卿华.镍基单晶合金力学特性及其在冷却涡轮叶片上的应用分析[D].南京:南京航空航天大学,2007.
[6]朱永新.带冠叶片摩擦减振特性研究[D].南京:南京航空航天大学,2007.
[7]丛佩红,张连祥,刘廷毅.航空发动机涡轮转子叶片锯齿形叶冠紧度的最佳选择[J].航空发动机,2000,21(4):9—12.
[8]王小宁,陈勇,欧阳华.带平行冠叶片的干摩擦阻尼特性研究[J].热力透平,2010,39(1):58—62.