Transonic Flow Around Compressor Rotor Blade Elements. Volume I. Analysis.
Final rept. 1 Dec 71-30 Jun 73,
GENERAL MOTORS CORP INDIANAPOLIS IND DETROIT DIESEL ALLISON DIV
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A numerical technique has been developed to obtain a solution for steady, transonic blade element flow in an axial compressor rotor of a turbomachine. Radius variation and stream surface convergence are included. The mixed-out exit conditions include shock wave losses and viscous mixing losses. The time-dependent Navier-Stokes equations in conservation law form are cast in a relative coordinate system suitable for describing rotor blade element flow. A discretized method of characteristics is used to determine the boundary conditions along the blade surface and exit plane. Steady, supersonic, uniform flow conditions are specified at upstream infinity, and periodicity is enforced on the remaining free boundaries. The hyperbolicparabolic system of equations describing the mixed flow problem are approximated by the explicit MacCormack finite-difference scheme. The time-dependent numerical solution rapidly converges to a steady-state result. Comparisons are made with experimental data for two-dimensional cascade flows and rotor blade element flow. Author
- Fluid Mechanics
- Jet and Gas Turbine Engines