Vane–Probe Interactions in Transonic Flows

Abstract In this article, a numerical investigation of the effect miniaturized five-hole probe downstream transonic low-pressure turbine vane row is presented. First, calibration was performed in uniform flow conditions, as case for any traditional calibration, wide range Mach number, yaw angle, and pitch angle conditions. The on general field throughout segments then evaluated by performing comparison between setup with vanes only (no probe) probes. It found that, traverses vane, impact isentropic number depends circumferential position. highest observed when located at upper mid-passage (θ = 0.5), consisting relatively small reduction suction side just 0.02. To assess accuracy quantities “measured” probe, probe-determined compared to vanes-only setup. A nonnegligible modification local distributions revealed respect undisturbed flow. Further involving stagnation point tracking showed that artificial high variation not caused outlet but induced nonuniform conditions vanes. With knowledge above, two-step correction used account effects nonuniformity flow, its 2D 3D regions. significative which difference from data reduced below 1 deg, except near endwalls where larger discrepancies remain due probe–endwall interactions. shortfall instead numbers. Finally, pitch-wise averaged were evaluated. differences occur radial gradients total pressure are stronger had almost negligible quantities.