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.
Transonic Flow Around Rotor Blade Elements
J. W. Kurzrock,
J. W. Kurzrock
Sundstrand Corp., Rockford, Ill.
A. S. Novick
Aerothermodynamics Department, Detroit Diesel Allison Division, General Motors Corp., Indianapolis, Ind.
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Kurzrock, J. W., and Novick, A. S. (December 1, 1975). "Transonic Flow Around Rotor Blade Elements." ASME. J. Fluids Eng. December 1975; 97(4): 598–605. https://doi.org/10.1115/1.3448139
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