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A Loss Model for the Transonic Flow Low-Pressure Steam Turbine Blades
Published January 01, 1987 by Institution of Mechanical Engineers in United Kingdom
A method is presented for predicting energy losses for the two dimensional turbine blade sections operating in transonic flow regions where the exit Mach number varies between 0.8 to about 1.6. A correlation method based on the cascade test data was used to establish the functional relations between the loss and blade geometry along with flow parameters. The basic profile loss model of Craig and Cox method for incompressible flow was adopted and modified for the effects of Mach number in the transonic flow regions. This modification takes into account the increases of losses at Mach number near unity due to boundary layer/shock interactions and possible flow separations. The losses due to flow incidence were correlated with the blade metal inlet angle and blade loading as parameters. The results of cascade test data for more than fifty low pressure steam turbine blade sections were used for establishing this loss model.