中文摘要：

目前航空发动机燃烧室雾化系统设计主要是针对亚临界喷射的,但高性能要求使得未来飞行器发动机的燃料喷射系统会以跨临界/超临界喷射为主。基于此,对液态碳氢燃料的超临界喷射特性进行了研究。首先选取了适合超临界流体物性参数特点的计算和求解方法,建立了超临界喷射特性计算的数学模型;然后采用该模型对JetA燃料喷射到N2环境中的喷射过程进行了数值计算研究,并通过与已有的实验结果进行对比验证了模型的正确性;最后对流动参数对于超临界喷射特性的影响进行了数值模拟,得到了喷射长度和喷射扩张角与流动参数之间的关系。

英文摘要：

Currently, the design of atomization systems for eombustors of aircraft engines is generally made for suberitical injection conditions. However, most of the injections will be supercritical or transcritical in future advanced aircraft for higher performance requirements. Therefore, this paper investigates the supercritical injection characteristics of liquid hydrocarbon fuel. Firstly, a numerical model incorporating the physical properties calculation method of supercritical fluid is developed for studying supercritical injection characteristics. The model is then employed for numerical investigations for the injection of JetA into N2. The calculated results are compared and validated against the available experimental data, showing an excel- lent agreement. The effects of flow parameters on supercritical injection characteristics are also studied with the numerical model and the variations of the injection length and jet spreading angle with flow parameters are obtained.