扩压段对高超声速推进风洞起动的影响

推进技术 ›› 2004, Vol. 25 ›› Issue (5): 430-434.

扩压段对高超声速推进风洞起动的影响

陈立红,张新宇,顾洪斌

中国科学院力学研究所北京100080;中国科学院力学研究所北京100080;中国科学院力学研究所北京100080

发布日期:2021-08-15
基金资助:
中国科学院仪器研制项目(Y00012);中国科学院创新方向项目(KJCX2 L01)资助。

Investigation for effect of supersonic diffusers on the start of the hypersonic propulsion test facility

Inst. of Mechanics, Academia Sinica,Beijing 100080,China;Inst. of Mechanics, Academia Sinica,Beijing 100080,China;Inst. of Mechanics, Academia Sinica,Beijing 100080,China

Published:2021-08-15

摘要/Abstract

摘要： 高超声速推进风洞是进行超燃冲压发动机模型地面模拟的重要试验设备。其中,扩压段的设计非常重要,它不是孤立的,而与主流系统和引射系统密切相关。通过对不同几何形状的扩压段在不同安装位置进行调试,研究在风洞起动过程中整个系统流动状态的演变规律,探索扩压段的优化设计。实验表明,扩压段应安装在距主喷管较近的位置,并具有与主喷管相匹配的入口面积和形状。扩压段的形状应设计成能使主气流通过一系列斜激波串减速的通道。扩压段应具有一定的长度以保证主气流减速到一定程度。

关键词: 超音速冲压喷气发动机;超高速风洞;超声速扩压段;模型

Abstract: Hypersonic propulsion test facility is important for the scramjet ground tests.The effect of the diffusers was investigated for the different shapes and sizes, as well as different locations.The start process of the facility for the different cases was under research in order to find the optimal configuration for the system.The experimental results show that the location of the diffuser should be close to the nozzle exit, and the shape and size of the diffuser entrance should match the nozzle exit.The configuration of the diffuser should be designed as a channel to allow the main flow pass through a shock train.The diffuser length should be long enough to ensure the main flow deceleration.

Key words: Supersonic combustion ramjet engine;Hypervelocity wind tunnel;Supersonic diffuser~+;Model

陈立红,张新宇,顾洪斌. 扩压段对高超声速推进风洞起动的影响[J]. 推进技术, 2004, 25(5): 430-434.