液体火箭发动机喷注器等流量喷孔流道的设计及验证

A DESIGN AND EXPERIMENT ON FLOW PASSAGE WITH EQUAL FLOW DISCHARGE ORIFICES IN INJECTORS OF LIQUID PROPELLANT ROCKET ENGINE

关键词:  液体推进剂火箭发动机  喷嘴  流量

Key words:  Liquid propellant rocket engine  Injector  Flow rate

摘要:

从横截面为矩形的管内分支流动的水动力学分析出发，结合层板式喷注器通道的特征，推导出等静压喷孔流道满足的常微方程。针对层流和湍流不同的流态沿程摩擦阻力系数的不同，方程无量纲化后，分别计算出了等静压喷孔的流道构型，并讨论了几何结构参数对设置等静压降喷孔的影响。参考计算得到的结构尺寸，设计和制作了若干变截面矩形流道及不同喷孔间距但喷孔直径和长度相同的试验件，通过改变压降，测量了各喷孔的流量分布。实验证实了模型的合理性。

Abstract:

A differential equation on orifices with the same injection pressure in astraight flow passage of rectangle cross section was deduced from hydredynamics ofmanifold flow by considering characteristics of flow passage of a platelet injector.Afterthe equation,became dimensionless, the configurations of flow passage were calculatedfor different friction coefficient in laminar and turbulent flow, respectively.Influence ofgeometry construction on design of orifices with equal injection pressure difference wasdiscussed.Referring to the construction dimensions calculated,serveral test parts of flowpassage,which had orifices of same diameter and length,but different passaage widthand space between orifices were designed and made.The theoretical model was proved reasonably by measuring the flow rate of each orifice of flow passages at various pressure difference.