CAJ | 학술논문

为了探索在一定补燃室长度条件下进气道直径大小对固冲发动机内流场的影响,采用了标准k-ε湍流模型和组分输运模型数值模拟了一设计的固冲火箭发动机掺混燃烧过程的内流场.结果表明:在一定补燃室长度和进出口条件下,存在一最佳进气道直径,能使空气与燃气完全掺混燃烧.在文中模拟条件下的最佳进气道直径为30mm.
위료탐색재일정보연실장도조건하진기도직경대소대고충발동궤내류장적영향,채용료표준k-ε단류모형화조분수운모형수치모의료일설계적고충화전발동궤참혼연소과정적내류장.결과표명:재일정보연실장도화진출구조건하,존재일최가진기도직경,능사공기여연기완전참혼연소.재문중모의조건하적최가진기도직경위30mm.
In order to research different diameters of air-inlet pipe's influences to the inside flow field of a solid rocket ramjet engine on a certain length of the afterburning chamber, this paper simulated the mixing and burning conditions in the afterburning chamber of a designed solid rocket ramjet engine by using the standard k-ε model and the species transport model. The results shows that under a certain length of the afterburning chamber and a certain in and out condition, there exists a corresponding diameter of the air-inlet pipe, which can make the mixing and burning situation in the afterburning chamber best of all. Under the simulated condition in this paper the most suitable diameter is 30mm.