当前位置: X-MOL 学术Propuls. Power Res. › 论文详情
Our official English website, www.x-mol.net, welcomes your feedback! (Note: you will need to create a separate account there.)
Effect of reacting gas on the fluidic thrust vectoring of an axisymmetric nozzle
Propulsion and Power Research ( IF 5.3 ) Pub Date : 2020-07-01 , DOI: 10.1016/j.jppr.2020.04.002
R. Chouicha , M. Sellam , S. Bergheul

During the last years, several thrust control systems of aerospace rocket engines have been developed. The fluidic thrust vectoring is one of them; it is simple in design and offers a substantial gain in weight and in performance. Numbers of studies that deal with this subject are conducted on cold gas flow model. It can be expected that the thermophysical properties of the gases may affect considerably the flow behavior. Besides, the effects of reacting gases at high temperatures, under their effects all flow parameters like to vary. This study aims to develop a new methodology that allows studying and analyzing the fluidic thrust vectoring for a reacting gas, by taking into account the effects chemical reactions on the flow parameters, such as separation point, reattachment point downstream and pressure distribution upstream the injection port. In this study, the thrust vectorization implying reacting hot gases was carried out by considering a chemical reaction mechanism. Reported study is based on Arrhenius reaction mechanism specific for H2–O2 propellant configuration. The thermodynamic parameters of the flow are calculated within the combustion chamber and different sections of the supersonic part of the nozzle. The results show a good agreement for cold gas, and as expected à slight difference for hot reacting gases. In parallel, in order to give more credibility to our work a study was carried out by numerical simulation for supersonic reactive and perfect flows in order to analyze the results of the method developed. In this work, the CFD performance of the fluidic thrust vectoring, has been qualitatively and quantitatively analyzed. Schlieren visualization and wall pressure results are compared to analytical and experimental findings.



中文翻译:

反应气体对轴对称喷嘴的流体推力矢量的影响

在过去的几年中,已经开发了几种航空火箭发动机的推力控制系统。流体推力矢量就是其中之一。它设计简单,并且在重量和性能上都有很大的提高。在冷气流模型上进行了许多有关此主题的研究。可以预料,气体的热物理性质可能会显着影响流动性能。此外,在高温下反应气体的影响,在它们的影响下,所有流动参数都喜欢变化。这项研究旨在开发一种新方法,该方法可以通过考虑化学反应对流动参数(例如分离点,下游的重新连接点和注入口上游的压力分布)的影响来研究和分析反应气体的流体推力矢量化。在这项研究中,通过考虑化学反应机理进行了暗示热气体反应的推力矢量化。报道的研究基于特定于H的Arrhenius反应机理2 –O 2推进剂配置。在燃烧室内以及喷嘴的超音速部分的不同部分内计算流的热力学参数。结果表明,对于冷气体而言,一致性很好,并且与预期的情况相比,对于热反应气体而言,略有差异。同时,为了使我们的工作更加可信,对超音速反应性和理想流动进行了数值模拟研究,以分析所开发方法的结果。在这项工作中,对流体推力矢量的CFD性能进行了定性和定量分析。将Schlieren可视化效果和壁压力结果与分析和实验结果进行比较。

更新日期:2020-07-24
down
wechat
bug