CAJ | 학술논문

采用PDF燃烧模型对头部两侧进气固冲发动机补燃室内流场进行数值计算，分析了高空和地面两种不同冲压喷管出口背压环境对冲压发动机二次燃烧的影响，并与试验结果进行了比较。利用该数值模拟方法分析了进气道出口形状、进气角度、飞行侧滑角等对发动机补燃室燃烧性能的影响，结果表明：进气道出口形状改为“肾形”可以改善补燃室绝热层的工作环境，但不利于补燃室内的掺混燃烧；随着进气角度的增加补燃室内的二次燃烧效率有所提高，但角度太大时弯头内侧有高温区出现；飞行侧滑角对该种进气形式的补燃室燃烧性能影响较大。
채용PDF연소모형대두부량측진기고충발동궤보연실내류장진행수치계산，분석료고공화지면량충불동충압분관출구배압배경대충압발동궤이차연소적영향，병여시험결과진행료비교。이용해수치모의방법분석료진기도출구형상、진기각도、비행측활각등대발동궤보연실연소성능적영향，결과표명：진기도출구형상개위“신형”가이개선보연실절열층적공작배경，단불리우보연실내적참혼연소；수착진기각도적증가보연실내적이차연소효솔유소제고，단각도태대시만두내측유고온구출현；비행측활각대해충진기형식적보연실연소성능영향교대。
Flowfield in afterburning chamber of solid ducted rocket with a head bilateral inlet configuration is simulated by using PDF combustion model under two different back pressure conditions, and the results are compared with test data. The influences of design parameters, such as the shape of inlet exit, inlet angle and the angle of sideslip on second combustion are investigated. The results show that the kid- ney-shap exit of inlet could improve the working atmosphere of thermal insulation layer but has unfavorable effect on mixed and combustion in chamber; the increas of the angle of inlet can improve the efficiency of combustion, but when the angle exceeds some value, zone of high temperature will be emerged ; the angle of sideslip has great effect on the performance of this kind of afterburning chamber.