采用端弯叶片对某弹用压气机静子的优化设计  

The Optimal Design for A Missile Engine Using End-bend Blade

作　　者：闫学慧[1] 杜涛[1] 

机构地区：[1]北京动力机械研究所,北京100074

出　　处：《战术导弹技术》2014年第6期75-80,共6页Tactical Missile Technology

摘　　要：为改善某型三级轴流压气机的气动性能,降低由端区附面层造成的流动损失,采用数值模拟的方法对具有不同几何进口角的端弯叶片进行了研究,分析了不同弯角对压气机性能及流动细节的影响。研究结果表明,具有合适弯角的端弯叶片可以改善端区流动、降低损失、拓宽工作范围,在不大幅提高工艺成本、不影响叶片强度的前提下可提高压气机气动性能。To improve the aerodynamic performance of a three-stage axial compressor and reduce the endwall loss of it,numerical simulation was used to elaborate the effect of end-bend blades with different geometry inlet angles. Several end-bend blades were studied to find out how the end-bend blades influenced the performance of the compressor and the aerodynamic details. The result showed that end-bend blades could improve the performance of the compressor without costing more,and the redesign did not cause any strength problems.

关 键 词：轴流压气机 端弯叶片 优化设计 

分 类 号：V23[航空宇航科学与技术—航空宇航推进理论与工程]