不同模型堵塞比的超声速风洞二次喉道优化  

Optimization on Secondary-Throat of Supersonic Wind Tunnel with Different Model Blockage

作　　者：冯美艳[1] 黄生洪[1] 

机构地区：[1]中国科学技术大学近代力学系,安徽合肥230026

出　　处：《推进技术》2012年第1期105-110,共6页Journal of Propulsion Technology

摘　　要：为了延长采用真空球排气系统的超声速风洞的工作时间,拟采用二次喉道提高真空球临界工作压强。本文针对Ma=4和Ma=7超声速风洞,采用计算流体软件系统地研究了不同发动机堵塞比对二次喉道起动能力的影响以及不同尺度的二次喉道对真空球临界工作压强的影响。研究结果表明,随着发动机堵塞比的增大,二次喉道的临界起动直径相应增大,呈非线性变化,同时,真空球的临界工作压强下降。因此,二次喉道直径应针对不同的模拟状态和发动机堵塞比范围综合优化选取。In order to increase the effective working time of vacuum ball exhaust system for supersonic wind tunnel with Ma = 4 and Ma =7, secondary-throat is utilized as a part of diffuser between test section and vacuum ball. To optimize the performance of vacuum ball exhaust system, two related aspects are numerically investigated with computational fluid dynamics software in this paper. The first is about the effects of blockage ratio （engine model vs. main nozzle） on cross area of seconda- ry-throat to start the supersonic wind tunnel while the other is about the effects of secondary-throat cross area on critical pres- sure （ maximum working pressure） of vacuum ball. It is concluded that the area of secondary-throat nonlinearly increases with engine/main nozzle blockage ratio, and the critical pressure is decreasing rapidly as well. The secondary-throat area should be optimized according to different engine/main nozzle blockage ratio and different testing Mach number.

关 键 词：超声速风洞 真空球 二次喉道 堵塞比 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]