Cavitation instabilities such as rotating cavitation and cavitation surge often occur in turbopump inducers for rocket engine. In the present study, a method for suppressing the cavitation instabilities in an inducer by jet injection is examined. Through eight nozzles placed at the upstream of the inducer, jets were injected in circumferential direction. The axial position of nozzles, speed of jet flow and direction of jet injection were changed. Through the experiments under various conditions, it was found that the occurrence regions of cavitation instabilities are decreased significantly with the injection in the same direction as shaft rotation with the jet flow rate about 10% of total flow. The flow field was also examined to clarify the mechanism for the suppression by injection. It was found that the incidence angle and cavity length were reduced by the injection, which decreases the occurrence region of instabilities.

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