double nozzle ejector 双嘴喷吸器
multi-nozzle ejector 多喷嘴引射器
exhaust-nozzle ejector 排气喷管引射器
multiple nozzle ejector 多喷嘴引射器
ejector nozzle 引射喷管
ejector on nozzle side 注嘴侧脱模销 ; 注塑模注嘴侧顶出
inlet ejector nozzle 进气引射式喷管
auxiliary inlet ejector nozzle 辅助进气引射式喷管
ejector supersonic exhaust nozzle 引射式超音速喷管
This paper presents an analytical method for calculating the flow field and performance of supersonic ejector nozzle.
本文介绍了超音速引射喷管的流场和性能的理论计算方法。
There exists an optimal exit area of secondary nozzle to result in a maximum thrust of rocket ejector in the light of the investigated ejector chamber structure.
在文中所研究的引射燃烧室结构条件下，存在一个最佳二次喷管出口面积，它能使引射火箭的推力达到最大。
From the experimental results the effects of nozzle axial position and mixer tube length upon ejector characteristic are revealed.
对实验结果进行分析，指出喷嘴轴向位置，混合管长度对引射器特性的影响。
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