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为了减小贮箱压力,要求火箭发动机的涡轮泵能够在低贮箱压力下工作。为此,涡轮泵通常在主叶轮前带有一个诱导轮。因此正确地预测诱导轮汽蚀性能很重要。迄今对在超低温推进剂,诸如液氢、液氧等中工作的诱导轮净正抽吸压头(NPSH)的预测做了不少研究,然而对不同超低温推进剂和不同尺寸诱导轮之间NPSH的预测方面的研究却很少。本文主要涉及这个问题。二个不同的诱导轮,一个用于液氢,另一个用于液氧,用液氮作工质进行试验,第三个诱导轮在不同的转速、流量系数和温度用液氢作工质进行试验。这三个诱导轮的NPSH都是在不同的流量系数下测定的。本文对液氢和液氮的汽蚀热力效应进行了比较,在液氢试验中所得的NPSH测量值和通过液氮试验所得数据所预测的值相当一致。
In order to reduce the tank pressure, the rocket engine turbo pump is required to operate at low tank pressure. For this purpose, the turbo pump usually has an inducer in front of the main impeller. Therefore, it is very important to correctly predict the cavitation performance of the inducer. Numerous studies have so far been made on the prediction of an induced wheel net positive suction head (NPSH) working in cryogenic propellants, such as liquid hydrogen, liquid oxygen, etc., however, NPSH has been studied between different cryogenic propellants and induction wheels of different sizes There is very little research on the predictions. This article mainly deals with this issue. Two different induction wheels, one for liquid hydrogen and the other for liquid oxygen, were tested using liquid nitrogen as the working fluid. The third induction wheel was operated with liquid hydrogen at different speeds, flow coefficients and temperatures test. The NPSH for these three inducer wheels were measured at different flow coefficients. This paper compares the thermal effects of vapor cavitation between liquid and liquid nitrogen, and the NPSH measurements obtained in the liquid hydrogen test are fairly consistent with those predicted from the liquid nitrogen test.