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Japan Aerospace and Exploration Agency has developed LE-5 engine(thrust 10∼14 ton class)，LE-7 engine(thrust 100 ton class)and its performances were reported in much literature. The thrust of LE-5 engine which has been used as he second stage of H-IIA rocket is about 10% smaller compared with LE-7 thrust. We developed a miniature pump which thrust is small 10% compared with LE-5 and it will be used as the orbit transfer of satellites in the future. However, pump performance data of 1 ton class thrust and design data of bearing, seal clearance for such a miniature pump were very few.
Therefore, in order to obtain the performance of very small pump for rocket engine, a miniature pump for liquid oxygen was designed and manufactured. The miniature pump was tested using liquid nitrogen. The test results showed that the pump rotated stably to the design rotational speed but seal leakage increased nearly about 75,000rpm.

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In the present paper the attention is focused on the relation between fan noise and velocity fluctuations of tip leakage flow around rotor blade of a low pressure axial flow fan. We measure time fluctuating velocity near the rotor tip around the rotor blades by using a hot-wire sensor from a relative frame of reference fixed to the rotor blades. As the results, it is clear that the velocity fluctuation due to tip leakage flow has weak periodicity and the heap portion appeared in its spectrum. If the flow rate was lower than the design condition, the tip leakage flow became to attach to the following blade and the sound pressure level was increased. At the maximum pressure operating point, the correlation between the velocity fluctuation due to tip leakage flow and acoustic pressure were increased.

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