高低空环境下压气机叶片颤振特性研究  

Research on Flutter Characteristics of Compressor Blades in High and Low Altitude

作　　者：张翔[1] 陈玉春[1] 黄秀全[1] 

机构地区：[1]西北工业大学动力与能源学院,陕西西安710072

出　　处：《推进技术》2015年第4期572-578,共7页Journal of Propulsion Technology

基　　金：国家自然科学基金(50706039);航空科学基金(2012ZB53022)

摘　　要：为了揭示高低空环境对压气机气动弹性稳定性的影响机理,采用谐波平衡技术和能量法对叶片在不同工作高度下的颤振特性进行了数值研究。结果表明:近失速二阶模态下叶片在地面和高空于不同的波节数1和2时达到最小气动阻尼状态;近失速前两阶模态下高低空叶片的气动阻尼系数(Log Dec)最小值分别为0.5460%,0.4521%和0.3460%,0.2168%,但叶尖处地面的当地Log Dec小于高空值;对于近失速一阶模态,叶片尖部的非定常压力脉动随着工作高度的变化呈现出不同的时空形态,从而导致当地积累功存在较大差异。In order to uncover the effect mechanics of high-low altitude on aeroelasticity stability of compres？sor,blades flutter characteristics in different altitudes were investigated through numerical study based on har？monic balance technique and energy method. Results show that,for the 2nd mode on the near stall point,the mini？mum aerodynamic damping of blades corresponding to nodal diameter has the value of 1 on the ground,while the value of 2 in high altitude. The minimum values of aerodynamic damping coefficient（LogDec）of blades were 0.3460%,0.2168%and 0.5460%,0.4521%,respectively,in high and low altitude for the first two modes on the near stall point,nevertheless,at the blade tip the local LogDec on the ground is less than this in high altitude. The unsteady pressure perturbations present various time-space shapes with different working altitudes at the blade tip corresponding to the first mode on the near stall point,which results in a huge discrepancy of local work sum？mation.

关 键 词：叶片颤振 非定常流 高低空 能量法 

分 类 号：V231[航空宇航科学与技术—航空宇航推进理论与工程]