Abstract
In a liquid rocket engine, cavitations around the inducer of the turbopump sometimes cause the instability phenomena when the inlet pressure decreases. The cavitation surge, one of the instability phenomena, has been discussed mainly "the inertia model". A data of the surge mode oscillation on a experimental turbopump in JAXA showed that its frequency was not changed continuously related to the decrease of inlet pressure, but changed disconnectedly. In this article, aiming at explaining this phenomena, an one-dimensional analysis is examined applying "an acoustic model" combined the inlet line with the sonic velocity of liquid oxygen.
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