摘要
在内径为30 mm的PDRE上,利用PDRE工作产生的余热对燃油进行加温,测量了不同温度下燃油的质量流量以及发动机的推力。实验结果和分析初步表明:①随着温度的升高,燃油流量先增加后减小;②推力随温度的升高而增大;③当燃油温度高于50℃时,比冲基本呈上升的趋势;④在流量相同时,比冲随温度的升高而增大;⑤当温度达到200℃,燃油喷入发动机时可以实现闪蒸状态,PDRE的性能参数更接近于理论值。
The introduction of the full paper discusses some recent relevant papers in the open literature, including some authored by us at NWPU, and then proposes the experimental investigations mentioned in the title, which are explained in sections 1 and 2. Section 1 briefly explains the experimental setup （Fig. 1 ） we have used for several years, Sections 2 is entitled ＂Experimental Results and their Analysis＂. Subsections 2.1, 2.2, 2.3 and 2.4 are respectively entitled ＂Analysis of Variation of Mass Flow with Temperature＂ （2.1）, ＂Initiation of Detonation＂ （2. .2 ）, ＂Analysis of Variation of Thrust with Temperature＂ （2.3）, ＂Analysis of Variation of Specific Impulse of Mix- ture（Kerosene/Oxygen） with Temperature＂ （2.4）. The experimental results, presented in Fig. 3 and Figs. 6 through 9, and their analysis show preliminarily that： （ 1 ） as the fuel temperature increased, the mass flow rate in creased first and then decreased; （2） the thrust augmented with the heated fuel temperature; （3） the specific im pulse augmented as the kerosene temperature exceeded 50℃ ; （4） when the mass flow rate was kept constant, the specific impulse increased with the heated fuel temperature; （5） as the kerosene temperature rose up to 200℃, the kerosene could reach the flash vaporization state when it was ejected into the engine and the performance parameter would be closer to the theoretical value.
出处
《西北工业大学学报》
EI
CAS
CSCD
北大核心
2011年第6期955-959,共5页
Journal of Northwestern Polytechnical University
基金
国家自然科学基金(509760945
1176158)
教育部博士点基金(20096102110022)资助
关键词
分析
控制
爆震
实验
燃油
测量
火箭发动机
煤油温度
比冲
analysis, control, detonation, experiments, fuels, measurements, rocket engines
kerosene tempera-ture, specific impulse
