预混可燃流体在大长径比圆管内流动传热点燃研究

FLOW, HEAT-TRANSFER AND IGNITION OF PREMIXED FLAMMABLE FLUID IN A LARGE LENGTH/DIAMETER RATIO TUBE

关键词:  变推力火箭发动机  燃料流  再点火  推力控制  燃烧试验

Key words:  Rocket engine with variable thrust  Fule flow  Reignition  Thrust control  Combustion test

摘要:

通过对预混可燃流体在大长径比圆管内的流动和传热的分析,首次提出一种用于脉冲火箭发动机多次点火的方法。新型发动机中,预混可燃流体在流动过程中被加热,并自动点火,按需要通过迅速散热保证熄火,从而实现了任意脉冲的自动点火和熄火,并可实现推力调节。对这种点火方法进行了理论分析和实验研究,成功地得到了5个工作脉冲。

Abstract:

This paper outlines a new approach for designing of multi-start aerospace engine. Thenew approach is motivated by analyzing flow, heat-transfer and ignition of flammable fluid in a certaindiameter long tube. The premixed flammable fluid is heated or cooled during its flow through thetube. Therefore, auto ignition and auto distinguish can be realized easily. By controlling the fluid massrate, the engine thrust is also be adjustable.A theoretical analysis model is also established. Analysis results show that the ignitioncharacteristics of the combustor are determined by tube length, diameter, temperature distribution,working condition and premixed flammable fluid property.Successful experiments have been done to prove this new method. Five performance pulses haveben achieved, of which each lasts about two seconds with interval between two pulses of fiveseconds.