高空模拟试车台超声速引射器数值研究

Numerical study on supersonic ejector of simulated altitude test stand

利用火箭发动机自身的超声速喷流作为引射气流的超声速引射器系统,在上面级火箭发动机高空试车台的研制中有着重要的应用价值,文中采用数值方法模拟求解了火箭发动机超声速引射器流场,比较了直管超声速引射器和有第二喉道的超声速引射器的性能、探讨了超声速引射器设计的影响因素。计算结果与实验结果符合较好,这表明该数值方法是研究超声速引射器的一种重要研究手段。

The supersonic ejector system, which adopts the supersonic jet of the tested rocket engine as the ejecting primary flow, plays an important role in upstage rocket engine test stand. This paper numerically solves the flow field of the rocket engine supersonic ejector, compares the capabilities of the straighttube ejector and the secondthroat ejector, and discusses the effect of the key design factors on the supersonic ejector. The calculated results agree well with the test results and it shows that the numerical methods can be used for the study of the supersonic ejector.