Transonic Flow Around Rotor Blade Elements

[+] Author and Article Information
J. W. Kurzrock

Sundstrand Corp., Rockford, Ill.

A. S. Novick

Aerothermodynamics Department, Detroit Diesel Allison Division, General Motors Corp., Indianapolis, Ind.

J. Fluids Eng 97(4), 598-605 (Dec 01, 1975) (8 pages) doi:10.1115/1.3448139 History: Received January 17, 1975; Online October 12, 2010


An analytical/numerical method for calculating blade-to-blade transonic flow fields around blade elements of an axial compressor rotor of a turbomachine is presented. Radius variation and stream sheet convergence are included. The analysis considers the time-dependent Navier-Stokes equations in conservation-law form which allows for viscous shock wave formation. A discretized method of characteristics is used to determine the boundary conditions along the blade surface and exit plane. An explicit, time-dependent, second-order, finite difference technique is utilized to numerically solve these partial differential equations in a transformed computational plane. Comparison of numerical results with cascade and rotor data indicate good agreement for blade surface pressure distributions and mixed-out exit conditions.

Copyright © 1975 by ASME
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