الفهرس 
Design and analysis of a single stage supersonic turbine with partial admission
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Abstract
Supersonic turbine is widely used in the turbopump of modern liquid rocket engines. Low mass flow rates and turbopump rotational speed requirements leads to the employment of the partial admission (PA) concept. A design of a supersonic turbine with partial admission is carried out using preliminary one-dimensional design and the two-dimensional method of characteristics.The partial admission concept is studied as well as several designs are analyzed and compared using Ansys-Fluent. The results show that optimum turbine efficiency has a weak dependency on the mean radius reduction for low blade heights due to the high PA ratios associated with it