Axial Thrust Analysis in Lox-Pump
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概要
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The LOX pump in the first stage of the next large launch vehicle, H-1 rocket, in Japan was developed by National Aerospace Laboratory and showed fairly good axial thrust performance. However, the behavior of the axial thrust is not well known because of the complicated mechanism of the thrust-balancing device. In order to reveal the flow characteristics in the thrust balancing device and to improve the device, the internal flow in the device is fully analyzed. The analysis developed here is confirmed to give satisfactory results by comparing with the measurements. Using the present analysis, the axial thrust behavior of the LOX pump is revealed for various combinations of balancing piston, balancing hole, swirl breaker and so on. The present analysis is applicable for any types of thrust balancing device.
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