叶根倒角对微小型离心压气机气动性能的影响  

Influence of Blade Root Fillet on Aerodynamic Performance of Miniature Centrifugal Compressor

作　　者：黄志浩 刘景源[1] HUANG Zhi-hao;LIU Jing-yuan(College of Aircraft Engineering,Nanchang Hangkong University,Nanchang 330063,China)

机构地区：[1]南昌航空大学飞行器工程学院,南昌330063

出　　处：《航空发动机》2020年第2期16-22,共7页Aeroengine

基　　金：国家自然科学基金(11102079、11562012)资助。

摘　　要：为了研究叶根倒角对微小型离心压气机流场及气动性能的影响,对1个带有分流叶片的微小型离心压气机进行数值模拟及理论分析。结果表明:叶根倒角最小角度对主叶片及分流叶片表面的静压分布影响不大,压气机总压比几乎不变,但效率提高明显,最大可提高0.99%。压气机效率的提高,一方面是由于通道涡的削弱减小了损失;另一方面是主叶片吸力面根部附近低速区减小和流线弯曲程度降低,提高了根部附近的流通能力,减少了横向流动,从而减小了二次流的损失。另外,叶根倒角最小角度变大,降低了叶片出口处气流的不均匀性,从而减小了损失。In order to study the influence of the blade root fillet on the flow field and the aerodynamic performance of the miniature centrifugal compressor,numerical simulation and theoretical analysis of a miniature centrifugal compressor with splitter blades were carried out. The results show that the minimum angle of blade root fillet has little effect on the static pressure distribution on the surface of the main blade and the splitter blade. The total pressure ratio of the compressor is almost unchanged, and the efficiency obviously increases by 0.99% at the maximum. On the one hand,the improvement of compressor efficiency is due to the weakening of the channel vortex to reduce the loss. On the other hand,the decrease of the low speed region near the suction surface root of the main blade and the decrease of the streamline bending degree improve the circulation ability near the root and reduce the transverse flow, thus reducing the loss of the secondary flow. In addition,the increase of the minimum angle of blade root fillet reduces the flow inhomogeneity at the outlet of blade, thus reducing the loss.

关 键 词：离心压气机 叶根倒角 最小角度 气动性能 数值模拟 航空发动机 

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]