Measurement of Pressure -Rise in a Pulse Detonation Engine

Measurement of Pressure -Rise in a Pulse Detonation Engine
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DOI:
10.2514/6.2009-857
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发表时间:
2009-01
期刊:
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影响因子:
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通讯作者:
A. Glaser;A. Rasheed;R. Dunton;V. Tangirala
A. Glaser;A. Rasheed;R. Dunton;V. Tangirala
中科院分区:
其他
文献类型:
--
作者:
A. Glaser;A. Rasheed;R. Dunton;V. Tangirala

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在脉冲爆震发动机(PDE)中进行了静压升和推力的实验测量。本研究采用了一个阀式乙烯-空气三管PDE,每管工作频率为20 Hz。介绍了脉冲爆震发动机压升的新术语和定义.使用低频和高频压力传感器对平均PDE击发静压进行定量。在燃烧室头部和尾部获得了直出口喷管和收敛出口喷管构型的压力测量值。确定高频压力测量提供了平均PDE击发压力的更准确测量。测试测量用于验证使用准一维极限环代码获得的计算预测。总体PDE压力上升被发现是敏感的系统流动损失和喷管的几何形状。据观察,在未优化的配置中,使用直出口喷嘴,PDE以总压力损失而不是压力增益运行。然而,当PDE包括一个锥形出口喷嘴时,观察到总的压力增益。PDE推力使用推力台直接测量推力,并使用管压力测量值计算推力。通过压力测量计算的推力被发现过度预测了推力站测量推力和计算推力预测。
*† ‡ § Experimental measurements of static pressure -rise and thrust are made in a pulse deton ation engine (PDE). The research employs a valved ethylene -air 3 -tube PDE at an operating frequency of 20 Hz per tube. New terminology and definitions for pressure -rise in a PDE are introduced. The mean PDE fired static pressure was quantified with both low and high frequency pressure sensors. Pressure measurements were obtained at the combustor head -end and tail -end for configurations with straight and converging exit nozzles. It was determined that the high frequency pressure measurements provided a more accurate measure of the mean PDE fired pressure. The test measurements are used to validate computational predictions obtained using a quasi -1D limit cycle code. The overall PDE pressure -rise was found to be sensitive to system flow losses and the e xit nozzle geometry. It was observed that in an un -optimized configuration, with straight exit nozzle, the PDE operated with an overall pressure loss instead of a pressure gain. However, an overall pressure gain was observed when the PDE included a conve rging exit nozzle. The PDE thrust was quantified using a thrust stand to measure thrust directly, and by using tube pressure measurements to calculate thrust. The thrust calculated by pressure measurements was found to over -predict both the thrust stand measured thrust and computational thrust predictions.