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.
出处
《战术导弹技术》
2014年第6期75-80,共6页
Tactical Missile Technology
关键词
轴流压气机
端弯叶片
优化设计
axial compressor
end-bend blade
optimal design
