A numerical modeling of endwall and tip-clearance flow of an isolated compressor rotor
Abstract
The current study is aimed at developing and appraising a numerical method for the development of endwall boundary layers through tip-clearances and their effect on the performance of an isolated compressor rotor. The Reynolds-averaged Navier-Stokes equation is solved for the entire flow field is elliptic form. The relative flow is computed on the generalized coordinates fixed on the rotor. Comparison between the numerical results and experimental data indicates that the complex three-dimensional viscous flow phenomena inside the tip region are properly predicted.
- Publication:
-
ASME, 30th International Gas Turbine Conference and Exhibit
- Pub Date:
- March 1985
- Bibcode:
- 1985gatu.confQ....H
- Keywords:
-
- Blade Tips;
- Compressor Rotors;
- Computational Fluid Dynamics;
- Three Dimensional Flow;
- Clearances;
- Computational Grids;
- End Plates;
- Flow Velocity;
- Navier-Stokes Equation;
- Viscous Flow;
- Fluid Mechanics and Heat Transfer