防冰引气对组合压气机性能影响的数值模拟研究  

Numerical Simulation Investigation on Influence of Anti-icing Bleed on Performance of Combined Compressor

作　　者：贺丹[1] 李杜[1] 张锦纶[1] 邹学奇[1] 

机构地区：[1]中国航空动力机械研究所,湖南株洲412002

出　　处：《航空发动机》2016年第5期63-69,共7页Aeroengine

摘　　要：为了研究防冰引气系统对轴流-离心组合压气机性能、内部流场和级间匹配关系的变化的影响,以带有防冰引气系统的组合压气机为研究对象,在离心压气机离心叶轮约3/4相对弦长位置轮缘处开槽引气,在轴流进口导叶叶片表面开孔喷气,进行3维数值模拟计算,并与不带引气和喷气系统的原始压气机进行对比分析。结果表明:防冰引气会引起组合压气机的性能降低,喘振裕度减小;轴流前2级由于折合转速下降,近工作点效率略有提高,但喘振裕度减小;离心级特性线向小流量方向移动,效率降低,稳定工作范围减小。In order to research the influence of the anti-icing system on the performance of axial-centrifugal combined compressor,the internal flow field and the variation of inter-stage matching relation, taking the combined compressor with anti-icing system as research object, bleeding by opening slot at about 3/4 relative chord position flange of centrifugal impeller for a centrifugal compressor, injecting air by making holes on vane blade surface of axial flow inlet, the three-dimensional numerical simulation of the combined compressor was carried out and the comparison between the combined compressor with and without the anti-icing system was performed. The results show that the anti-icing system causes the degeneration of compressor performance and stall margin. Due to the decline of corrected rotation speed, the efficiency of the first and second axial stage is increased but the stall margin is decreased. The performance curve of the centrifugal compressor is moved towards low mass flow, the efficiency and the steady operation range are reduced.

关 键 词：组合压气机 防冰引气 喷气 数值模拟 航空发动机 

分 类 号：V211.6[航空宇航科学与技术—航空宇航推进理论与工程]