某小型涡扇发动机增压级设计与试验验证  

Design and experiment demonstration of a booster of small turbofan engine

作　　者：丁建国[1] 邹学奇[2] 吴志青[2] 杨晶晶[2] 胡骏[1] 

机构地区：[1]南京航空航天大学能源与动力学院,南京210016 [2]中国航空动力机械研究所,株洲412002

出　　处：《航空动力学报》2008年第8期1519-1522,共4页Journal of Aerospace Power

摘　　要：采用经过试验验证的一维方案设计程序包以及与轴对称流设计程序相匹配的任意中弧线叶片造型程序,运用三维计算与一维、二维气动设计相结合的方法成功地完成了某小涡扇发动机增压级气动设计,并且单独设计和加工内涵两级增压级进行了试验验证,试验结果表明,该增压级具有宽广的高效率区和高喘振裕度,设计结果与试验结果吻合较好.By means of test-proven one dimension project design procedure library and arbitrary airfoils blade design procedure of turbo machine matching the axial symmetry streamline curvature approach design code, a booster of small turbofan engine was designed and tested successfully by combining three dimension computational fluid dynamics, one dimension and two dimension aero-dynamics designs. The experiment results indicate that, the booster has high efficiency over a wider range and better stall margin, and the design results correspond with experimental results.

关 键 词：增压级 设计 小型涡扇发动机 试验验证 

分 类 号：V231[航空宇航科学与技术—航空宇航推进理论与工程]