压气机动叶CLOCKING效应对叶片可靠性影响的数值研究  

Numerical Research on Effect of Rotor CLOCKING on Blade Security in Compressor Stages

作　　者：姚宏伟[1] 颜培刚[1] 韩万金[1] 

机构地区：[1]哈尔滨工业大学能源科学与工程学院,哈尔滨150001

出　　处：《汽轮机技术》2011年第4期271-273,共3页Turbine Technology

摘　　要：采用基于谐函数(harmonic)的非定常计算方法,数值模拟了某型燃气轮机中间三级轴流压气机流场,研究第二级动叶CLOCKING效应对中间级静叶片气动负荷的影响。通过对各列叶片非定常气动力和气动力矩进行时域分析,指出不同CLOCKING位置对应的气流激振力对叶片的气动负荷造成了明显的影响。进行了中间级动叶和静叶的振动可靠性分析。计算结果表明,该压气机的3组静叶片避开共振区的程度各不相同。R2转子叶片处于不同的CLOCKING位置会引起下游S2静叶片气流激振力发生显著变化,导致S2叶片产生比较强烈的共振。The field of three stages in axial compressor for a gas turbine was simulated by the unsteady calculation method based on harmonics. The impact of the clocking effect of rotor blade in second stage on aerodynamic load of static blade in mid stage was investigated. Through analyzing the unsteady aerodynamic forces and moments of the blades in time-domain and frequency domain, pointed out that the location of different CLOCKING corresponding flow induced force have significant impact on the aerodynamic load of blade. In the CLKO position, the static blade in mid stage in some time get conventional force in the opposite direction, and the amplitude of the fluctuations for aerodynamic force and moment to be maximum. It is shown that the three stage compressor has been made in the structure of static natural frequency of blade area as possible to avoid resonance, but different static blade void the resonance in different degree, which may be responsible for the fatigue of S2 blade wllen R2 at CLOCKING position.

关 键 词：压气机 非定常 CLOCKING效应 气流激振力 气动负荷 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]