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针对采用下颌式进气道的固体火箭冲压发动机,建立了二次燃烧性能计算模型,对掺混燃烧性能进行了仿真研究。研究表明,采用掺混装置可大幅提升下颌式进气道的固冲发动机补燃室一次燃气和空气的掺混均匀度,并通过数值仿真对掺混装置进行了优化。结合数值仿真优化结果,通过地面直连试验,验证了不采用与采用掺混装置的补燃室二次燃烧性能。试验结果表明,合理设计掺混装置,可显著提高补燃室二次燃烧性能,特征速度燃烧效率均在93%以上;空燃比在6~20之间的发动机高空比冲提升了55%以上,空燃比在20~30之间的发动机高空比冲提升了75%以上。
Aiming at the solid rocket ramjet engine with jaw inlet, the calculation model of secondary combustion performance was established and the simulation of blended combustion performance was carried out. The results show that the mixing device can greatly improve the uniformity of primary gas and air in the afterburner of the impulse combustion chamber of the jaw inlet, and the optimization of the mixing device is carried out by numerical simulation. Combining with the numerical simulation and optimization results, the secondary combustion performance of the afterburner without and with the mixing device was verified by the direct-on-ground test. The test results show that the rationality of the design of the mixing device can significantly improve the secondary combustion performance of the afterburner, the combustion efficiency of the characteristic speed is over 93%, and the engine altitude over-air-lift of the air-fuel ratio between 6 and 20 is increased by 55% The air-fuel ratio of 20 to 30 between the engine altitude thrust increased more than 75%.