Abstract
An inviscid base pressure model for transonic turbine blade has been presented. It has been shown that for a given back pressure the base pressure at the trailing edge, and the profile loss of a turbine blade are fixed according to the model and the base pressure can be calculated with the help of an inviscid numerical scheme. A parameteric study on the model shows that a blade profile with positive curvature downstream of the throat is advantageous for generating less loss, whilst the worst situation is when the exit flow reaches the sonic condition.
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References
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Liping, X. An inviscid model for the base pressure of transonic turbine cascade. Acta Mech Sinica 7, 39–45 (1991). https://doi.org/10.1007/BF02486594
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DOI: https://doi.org/10.1007/BF02486594