高负荷静子表面附面层抽吸试验研究  

Experimental study on boundary layer suction of highly loaded stator

作　　者：李丽丽 刘太秋 傅文广 孙鹏[2] 徐文峰[2] 

机构地区：[1]中国航发沈阳发动机研究所,沈阳110015 [2]大连海事大学轮机工程学院,辽宁大连116026

出　　处：《大连海事大学学报》2018年第1期107-112,共6页Journal of Dalian Maritime University

基　　金：国家自然科学基金面上项目(51576024);国家自然科学基金重点项目(51436002)

摘　　要：为掌握高负荷静子内部流动特征,研究附面层抽吸对静子性能流动的影响,采用数值和试验相结合的方法,对高负荷末级吸附式静子的气动性能开展研究,分析高马赫数来流条件下的静叶气动性能,研究叶片表面附面层抽吸对高负荷静子气动性能的影响.研究表明:随着吸气量的增加,静子的气流折转能力增加,落后角减小2°~3°;静子的减速扩压能力增加,出口马赫数减小0.03~0.07;吸气量增加到0.08 kg/s时达到最佳值,此时,静子落后角和出口马赫数达到最小值;进一步增加吸气流量,落后角、马赫数反而增大.In order to understand the flow characteristics in highly loaded stator and study the influence of the boundary layer suction on the aerodynamic performance in stator,the experimental and numerical methods were adopted for aerodynamic performance analysis of a final stage stator cascade of a highly loaded fan. Aerodynamic performances of the stator cascade under high incidence Mach number were analyzed.The influence of boundary layer suction on the aerodynamic performance in highly loaded stator was studied. Results show that with the increase of suction mass flow,the turning ability of airflow increases,the deviation angle decreases 2° - 3°;the capability of pressure diffusion increases,and the outlet Mach number decreases 0. 03 - 0. 07; the optimum value was reached when the suction mass flow increases to 0. 08 kg/s,the deviation angle and the outlet Mach number decrease to the minimum,but when the suction mass flow continues increasing,the deviation angle and the outlet Mach number increase.

关 键 词：高负荷静子 附面层抽吸 落后角 出口马赫数 吸气量 

分 类 号：V231.1[航空宇航科学与技术—航空宇航推进理论与工程] U664.131[交通运输工程—船舶及航道工程]