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为确定真空舱——扩压器装置内喷管出口位置对起动压力比和舱压比的影响,进行了无诱导流的引射器的特性试验。用锥型和特性两种喷管,将一个不变直径扩压器与几种第二喉道扩压器组合成型面不同的引射器,研究了这些组合下喷管出口面位于扩压器区域及位于真空舱区域内的两种情况。用 Korst 流动模型,作了简单的分析,近似地解释了所观察到的这种真空舱压变化与喷管出口位置之间的相互关系。结果表明;当锥型喷管和扩压器相对位置合适时,引射器起动压力此和分离压力比的实验值与用 German 等人的方法得到的计算值基本一致。
In order to determine the effect of nozzle outlet position in the vacuum-diffuser device on the starting pressure ratio and the cabin pressure ratio, a characteristic test of an ejector with no induced flow was performed. Using a conical and characteristic nozzle, an invariant diameter diffuser and several second throat diffusers were combined to form ejectors with different profiles. It was studied that the outlet face of the nozzle under these combinations was located in the diffuser Area and the vacuum chamber area in both cases. A simple analysis using the Korst flow model gives an approximate explanation of the correlation observed between the change in vacuum chamber pressure and the nozzle exit position. The results show that when the relative position of conical nozzle and diffuser is proper, the experimental values of ejector start-up pressure and separation pressure ratio are basically the same as those obtained by the method of German et al.