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Abstract
The LOX pump in the first stage of Japan's next large launch vehicle H-II was developed by NAL and showed fairly good results in both the overall performance and thrust balance. However, the behaviour of the thrust balanching device is not well known because of the complicated flow in the thrust balancing device. In order to obtain a better understanding and to determine the mechanism of thrust balance, the internal flow in every part of the LOX pump in fully analysed together with the overall pump performance. The present method gives satisfactory results to the pump overall performance and the axial thrust behaviour. The analytical method developed here is easily applicable to any other types of thrust balancing devices.
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