Abstract
A new throughflow calculation method using the time marching numerical technique is presented and compared with other prediction methods for a low hub: tip radius ratio transonic nozzle. It is shown that the accuracy of the method is limited primarily by the assumption of a camberline flow angle in the blade-to-blade plane. A method which iterates between the meridional and blade-to-blade planes is also presented and it is shown that the predictions compare well with a full 3D theory for a twisted transonic nozzle with high casing flare. Blade surface pressures have been measured experimentally for this case using a transonic annular cascade and the agreement between theory and experiment is found to be good. Despite the fact that the iterative method is an approximation to the full 3D method, due to the neglect of stream surface twist, it has the advantages that it uses less computer time and storage.
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