多级压气机动叶不同周向位置下叶片动应力及响应计算  

Numerical Research on Blade Dynamic Stress And Resonance Under Different Rotor Circumferencial Positions in A Multi-stage Compressor

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6期412-414,475,共4页Turbine Technology

摘　　要：对多级压气机进行非定常计算,数值模拟了某型燃气轮机中间三级轴流压气机流场,研究第二级动叶处于不同周向安装位置下中间级静叶片动应力及响应,指出动叶不同周向位置对应的气流激振力对叶片的气动负荷以及动应力造成了明显的影响,特别是在对叶片构成危险性最大的一阶低频共振点,动叶片处于CLK0安装位置时的激振力对叶片应力和位移响应幅度影响程度都明显要大于其它安装位置的情况,同时导致S2叶片产生比较强烈的共振,造成结构上的疲劳损伤。This paper carried out unsteady calculation for Multi-stage compressor, numerical simulated the flow of middle three-stages of axial compressor in a certain type of gas turbine, and studied the dynamic stress and response of intermediate stage blade with the second stage rotor blade mounted different circumferential direction, study pointed out the exciting force corresponding to the rotor blade at different circumferential direction had significant effect on aerodynamic load and dynamic stress of the blade, especially, at the first-order and low-frequency resonance point having highest risk for the blade. Study found,when the rotor lied at CLKO installation location, the exciting force had more significantly effect on the stress and displacement response amplitude of blade than other installation locations, meantime causing a relatively strong resonance.

关 键 词：压气机 非定常 动应力及响应 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]