Computation of End-Wall Flow in a Linear Cascade and Comparison With Experiment

Viscous flow computations were performed with an explicit Runge-Kutta flow solver, with the aim to predict the loss distribution downstream of a set of compressor blades in cascade. The code solved the thin-layer Navier-Stokes equations in generalized coordinates, and the turbulence field was characterized with an eddy-viscosity turbulence model. Comparisons were made of the computed and measured total pressure loss distribution at various spanwise locations, two axial chords downstream of the trailing edges. Additional comparisons of the predicted three-dimensional velocity field, with three-component laser-Doppler-velocimetry measurements, were performed at a cross-stream plane twenty-two percent of a axial chord downstream of the trailing edges. At the near design test condition, good overall predictions of the total pressure loss, and axial velocity profiles were achieved. Satisfactory predictions of the secondary flow resulted. The prediction of blade-surface pressure distribution and total-pressure losses at increasing incidence progressively deteriorated. Besides validating the code, with an incompressible test case, the main aim of this investigation was to calibrate the code at off-design conditions prior to progressing to the more challenging, and unsteady, case of cascade stall.