激波管风洞中全尺寸涡轮试验的若干气动问题  

SOME AERODYNAMIC CONSIDERATIONS ABOUT FULL SCALE TURBINE EXPERIMENTS IN SHOCK TUBE TUNNEL

作　　者：季路成[1] 杨吉民[1] 徐建中[1] 

机构地区：[1]中国科学院工程热物理研究所,北京100080

出　　处：《工程热物理学报》2002年第1期52-54,共3页Journal of Engineering Thermophysics

基　　金：中国科学院知识创新工程咨助项目;国家自然科学基金资助项目(No59906012)

摘　　要：暂冲式涡轮实验台是促进涡轮部件技术进步的关键设施．本文对激波管风洞全尺寸涡轮实验台若干气动问题进行了研究，结果表明：在暂冲式风洞中，涡轮建立稳态流场所需时间正比于涡轮叶排的轴向尺寸和折合流量．激波管风洞、喷管、实验段间匹配非常关键．Short Duration Turbine Test Rig is a key facility to promote turbine technology. Some Aerodynamic investigations about full scale turbine experiments in shock tube tunnel are presented. It is shown that the time used to establish stable turbine flow-field in the short duration wind tunnel is proportion to the axial length of the whole turbine and corrected mass flow rate. The matching of shock tube, nozzle and test section is very important.

关 键 词：短工作周期风洞 激波管风洞 涡轮试验 航空发动机 气动问题 全尺寸 

分 类 号：V211.751[航空宇航科学与技术—航空宇航推进理论与工程] O351.2[理学—流体力学]