基于试验设计的固体火箭冲压发动机燃烧效率规律研究

Research of solid ducted rocket combustion efficiency based on design of experiment methodology

以双下侧进气布局的固体火箭冲压发动机为研究对象,以补燃室中燃气与空气的掺混燃烧效率规律为研究目标,将燃气喷管数量、补燃室头部距离、补燃室长径比、空气进气角度、空气进气速度5个因子作为二次燃烧效率的影响因子,基于试验设计方法,建立了5因子2水平的全因子试验表,并以该表为基础对构建出的32种不同掺混结构的固体火箭冲压发动机补燃室的反应流场进行数值模拟。用试验设计中的数据处理方法对计算结果进行分析,获得了5个显著因子及各因子对燃烧效率的影响规律。为了验证分析结果的正确性,从试验设计表中选取5种掺混结构进行了地面连管试验,试验结果与分析结论一致。将试验设计方法应用到固体火箭冲压发动机燃烧性能的研究中,为发动机性能寻优提供了新途径,具有较高的工程应用价值。

To study the combustion efficiency of air and primary fuel in the combustor of solid ducted rocket with twin--90° ventral 2D inlets, five factors including numbers of fuel inlets, dome height, rate of the length of combustion and diameter,air-flow angle and air-flow velocity are selected as the influence factors of secondary combustion efficiency. And, the five-factor and two-level table is established based on design of experiment （DOE） methodology. Flow fields of 32 combustors with dif- ferent structures in above DOE table are studied by numerical simulation. Then, the simulation results are analyzed by using data processing procedure of DOE and the effect of five factors on combustion efficiency Js obtained. To validate the results of simulation,performance of five different combustors in the DOE table are tested in the direct-connect experiment facility and the simulation result matches up well with the experiment result. In this paper, the DOE methodology has been successfully applied in the research of combustion performance of solid ducted rocket, and supplies a new feasible approach for the improvement of engine performance. It can be concluded that the research in this paper is valuable in the domain of engineering application.