非对称安装布局下大型高超声速风洞引射增强型二次喉道数值优化  

Numerical Optimization on Ejection-Supercharged Second Throat of Large Scale Hypersonic Wind Tunnel under Asymmetric Model Installation

作　　者：陈缘 黄生洪[1] CHEN Yuan;HUANG Sheng-hong(Key Laboratory of Mechanical Behavior and Design of Materials,School of Engineering Science,University of Science and Technology of China,Hefei 230026,China)

机构地区：[1]中国科学技术大学工程科学学院材料力学行为与设计重点实验室,安徽合肥230026

出　　处：《推进技术》2022年第9期168-175,共8页Journal of Propulsion Technology

摘　　要：增强二次喉道扩压能力,降低接力引射器的引射流量是提高大型高超声速风洞运行经济性的重要技术措施。引射增压型二次喉道通过在二次喉道侧壁引射低总压介质增强其扩压能力,是一种非常有潜力的实用方案。本文通过数值模拟研究了其在长模型大攻角等非对称安装布局条件下的运行流场,并进一步优化了压力、介质类型等引射条件。结果表明,优化方案在高超声速风洞复杂运行条件下仍能保持较高的二次喉道扩压能力,较大幅度降低接力引射器的引射流量,具有可行性和实用性。Reducing the flow rate of the relay ejector with promotion of pressure recovery capacity of the secondary throat is an important technology of improving the operation economy for large-scale hypersonic wind tunnel.The ejection-supercharged secondary throat diffuser is a very potential and practical scheme,which can enhance its pressure recovery capacity by ejecting low total pressure medium into the side wall.Numerical simulations on ejection diffusion flow fields of the hypersonic wind tunnel with such an ejection-supercharged secondary throat diffuser under asymmetric installation of a long model with large attack angle were conducted,and the ejection parameters including pressure and medium types of ejector in diffuser were optimized.The results show that the optimized ejection-supercharged secondary throat diffuser scheme can maintain a high pressure recovery capacity under the practical complex wind tunnel operating conditions and save the ejection flow rate of the rear relay ejector to a large degree,providing better feasibility and practicability.

关 键 词：高超声速风洞 非对称 二次喉道扩压器 引射 数值模拟 

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]