栅距非谐对跨声速压气机转子气动阻尼的影响  

Effects of Pitch Mistuning on Rotor Damping of Transonic Compressor

作　　者：杨晓东[1] 侯安平[2] 李漫露 刘马成[2] 

机构地区：[1]北京机电工程研究所,北京100074 [2]北京航空航天大学能源与动力工程学院/航空发动机气动热力国家重点实验室,北京100191 [3]中航空天发动机研究院有限公司,北京101304

出　　处：《推进技术》2017年第1期94-102,共9页Journal of Propulsion Technology

基　　金：国家自然科学基金重点资助项目(60934001)

摘　　要：为了提高跨声速压气机的气动弹性稳定性,针对跨声速颤振实验转子提出了栅距交替非谐布局方案,基于能量法建立了其全周气动阻尼计算模型,数值研究了栅距非谐对气动阻尼的影响。计算了谐调转子的气动性能、颤振边界和叶片模态,其结果和实验数据吻合较好,比较了谐调及非谐转子气动性能,发现栅距非谐会造成转子气动性能有所降低,随着非谐量的增加,性能降低越明显;在研究的非谐条件下,压比最大相对降低0.30%,效率最大降低0.54%。对于该转子的平均气动阻尼,栅距非谐使得转子在大部分甚至整个叶片间相角区域内气动阻尼均有所提高,最大达到37%。通过对叶片表面不同叶高的非定常压力以及积分气动力研究表明,栅距交替非谐对转子相邻两个叶片稳定性的影响存在差异,并且非谐量越大,差异越明显。Based on transonic compressor flutter test rotor,a pitch mistuning method is investigated to improve the aeroelastic stability of transonic compressor. The effects of pitch mistuning on rotor aerodynamic damping are obtained based on energy method with a full-annulus aerodynamic damping computational model. Numerical results of rotor performance,flutter margin and blade mode of tuned rotor are respectively consistent with experiment results. Compared with results of tuned rotor,pitch mistuning leads to lower aerodynamic performance and this tendency becomes more significant as mistuning level increases,and the maximum decline of pressure ratio and efficiency is 0.30% and 0.54% respectively,while average damping increases during most inter-blade phase angles（IBPA） with a maximum increase of 37%.Investigation of unsteady aerodynamic pressure and integral aerodynamic forces shows that pitch mistuning affects aeroelastic stability of adjacent blades differently,and the differences become more apparent with a high-level mistuning.

关 键 词：栅距非谐 气动阻尼 颤振 能量法 气动弹性稳定性 

分 类 号：V231.2[航空宇航科学与技术—航空宇航推进理论与工程]