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J. L. Le H. C. Bai A. A. Mishunin A. V. Starov 《Combustion, Explosion, and Shock Waves》2003,39(3):292-299
Results of an experimental study of a full scramjet model operating on kerosene, which was performed in an IT-302M hotshot wind tunnel based at the Institute of Theoretical and Applied Mechanics of the Siberian Division of the Russian Academy of Sciences, and an experimental study of a model operating on hydrogen, which was performed in a hotshot wind tunnel with fire heating based at the China Aerodynamic Research and Development Center, are reported. The tests were performed for Mach numbers 5 and 6 for flow parameters close to in-flight conditions. An optimal system for kerosene injection under these conditions was determined, and the thrust characteristics of the engine model were examined. The possibility of controlling kerosene combustion in tests in the short-duration wind tunnel was analyzed, and special features of fuel ignition in a short combustor were considered. Intense combustion of kerosene was achieved with upstream injection of more than 3% of hydrogen, which allowed obtaining effective thrust. The distributions of static pressure and force characteristics of the model in the case of kerosene and hydrogen combustion were compared. 相似文献
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超燃冲压发动机一维跨声速流动方程在临界声速点存在奇异问题,现有的基于L’Hosp ital法则的求解方法在进行跨声速流动计算时可能出现较大的数值误差.从数值稳定性和误差特性两个方面对该算法进行了分析,结果表明问题主要在于方程的奇异初值误差,需要针对这一问题提出改进算法. 相似文献
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IntroductionMixing of fuel with oxidizer and their combustionare encountered in many engineering applicationsincluding hypersonic propulsion system in space vehicles.Particularly, the fuel injection scheme in hypersonicvehicles incorporating Scramet (Supersonic CombustionRamjet) engines, requires special attention for efficientmixing and stable combustion. Though a considerablenumber of researches has been cwhed out on ndxing andcombustion of fuel with oxidizer in Scramet program,still it fa… 相似文献
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基于一种固体燃料超燃冲压实验发动机的实验数据,使用数值模拟软件分别对超燃冲压发动机燃烧室的初始状态以及启动后的燃烧流动进行数值模拟。采用用户自定义函数方式给定PMMA燃料进口边界。数值模拟结果显示:燃烧室流场特性分布符合理论分析;燃烧室固体燃料壁面的燃料退移速率与实验数据有一定差异,但是整个燃面沿轴向的燃速分布规律与实验值近似;沿轴向的燃面附近的压力分布与实验结果较为吻合。研究结果表明:该数值计算模型较为合理,对固体燃料超燃冲压发动机的理论研究具有一定参考价值。 相似文献
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超燃冲压发动机尾喷管设计方法研究 总被引:2,自引:1,他引:1
本文应用最小喷管长度理论对二维超燃冲压发动机尾喷管上壁型线进行了设计,并对尾喷管性能进行了计算,应用粒子群优化算法对所设计的喷管型线进行了优化。为超燃冲压发动机尾喷管几何参数的选择提供了参考范围。 相似文献
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In this paper,a small flow rate hydrocarbon turbine pump was used to pressurize the fuel supply system of scramjet engine.Some experiments were carried out to investigate the characteristics of turbine pump driven by nitrogen or combustion gas under different operating conditions.A experimental database with regard to the curves of the rotational speed,mass flow rate and net head with regard to centrifugal pump were plotted.These curves were represented as functions of the pressure and temperature at turbine inlet/outlet and the throttle diameter at downstream of centrifugal pump.A sensitivity study has been carried out based on design of experiments.The experimental was employed to analyze net head of centrifugal and throttle characteristics.The research results can accumulate foundations for the close loop control system of turbine pump. 相似文献