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A cryogenic test facility has been developed to perform inducer and pump tests using liquid nitrogen. Performance tests of a turbopump in the maximum 50ton-thrust class can be performed with cryogenic fluid in the facility which operates at a temperature around -196℃ with the rotational speed up to 30,000rpm. To verify the reliability of the cryogenic pump test facility, hydraulic performance tests of an inducer were accomplished, and their results were compared with the result from a water test. The results confirm the reliability of the cryogenic test facility, and it is expected to contribute for on-going development of a turbopump for liquid rocket engines.
In this study, the effect of volute area distribution on the performance of a centrifugal pump were numerically studied using a commercial CFD code. To reduce the shutoff head, maintaining head and efficiency at a design flow rate, the flat head-capacity characteristic curves in which the head varies only slightly with capacity from shutoff to design capacity are frequently required. In order to control the shutoff head of a pump, several volute cross-sectional area distributions were proposed as a main parameter with the same impeller geometry. The calculation results show that the slope of the performance characteristic curve of the centrifugal pump can be controlled by modifying the area distribution from volute tongue to volute outlet with fixed volute outlet area and also varied volute outlet area.
An analytic solution is given to the unsteady compressible boundary layer flow induced by periodically oscillating perturbation about its axis on the steadily rotating disk. The flow is determined by two different physical mechanisms : (1) energy diffusion process across the Ekman layer; (2) typical Ekman layer flow similar to incompressible case. Those mechanisms give rise to distinctively separating flow structure and characteristics from incompressible case, i.e. the counterpart of compressible flow. It shows that, if the fluid is compressible, the resonant flow is localized and the position depends on frequency of the oscillating disk.
A supersonic separator is a cutting-edge technology that swirls the flow and induces temperature difference to dehydrate natural gas. Since the geometrical configurations of blade considerably affect the performance of a supersonic separator, thermal-flow fields should be thoroughly investigated. In this study, the swirling performance and consequential thermal effects of a supersonic separator were numerically investigated using the commercial computational fluid dynamics (CFD) code, ANSYS CFX. The streamline, velocity, pressure, and temperature distributions were graphically depicted with various types of the blade. Moreover, the pressure loss coefficient and swirling intensity were presented to evaluate the performance of a supersonic separator.