Abstract
The paper presents a numerical and experimental study of stall propagation in axial compressors. In the numerical study, the compressor blades are represented as an isolated linear cascade of airfoils, and the stall propagation is simulated using a vortex tracking method. This method involves the use of periodic vortex arrays to simulate infinite cascades, the use of a vortex merging algorithm to allow computations for large times, the imposition of the no-slip and the impenetrability boundary conditions in an integral sense, the use of integral boundary-layer methods to locate the separation points, and the use of Fourier decomposition to compute the velocities of the propagating stall. Detailed parametric studies have been performed to analyze the influence of flows parameters such as the inflow angle and stall wavelength and geometric parameters such as cascade solidity, blade camber, and stagger. The experimental investigations were conducted in a single-stage axial compressor test rig. The occurrence of rotating stall in this research compressor was demonstrated, and some experimental studies on the effect of various flow parameters on the stall propagation were conducted. The computational and experimental results are compared and are shown to be in qualitative agreement.
Original language | English |
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Pages (from-to) | 1945-1952 |
Number of pages | 8 |
Journal | AIAA journal |
Volume | 28 |
Issue number | 11 |
DOIs | |
State | Published - Nov 1990 |