Validation Studies of Linear Oscillating Compressor Cascade and Use of Influence Coefficient Method

Abstract

Advanced predictions of blade flutter have been continually pursued. It is noted however that validation cases of unsteady CFD methods against experimental cases with detailed 3D unsteady pressures are still rather lacking. The main objectives of the present work are two-folds. First, validate and understand the characteristics of blade tip clearance, as well as a bubble-type flow separation for an unsteady CFD solver against a 3D oscillating cascade experiment. And second, examine the applicability of the influence coefficient method (ICM) as widely used in an oscillating linear cascade setup. In the first part, the capability of a widely used commercial solver (CFX) for unsteady flows induced by a 3D oscillating compressor cascade is examined. The present computations have shown consistently a destabilizing effect of increasing blade tip clearance, in agreement with the experiment. More remarkably, the computational analyses reveal a distinctive interplay between the inlet endwall boundary layer and the tip clearance in relation to the aerodynamic damping. Different inlet endwall boundary layer thicknesses are shown to lead to qualitatively different aeroelastic stability characteristics in relation to tip clearance. The aero-damping variation with the tip clearance under the influence of the inlet endwall boundary layer seems to correlate closely to a balancing act between the passage vortex and the tip leakage vortex. The tip clearance aeroelastic behavior seems also in line with a simple quasi-steady analysis. On the other hand, the mid-chord laminar bubble separation on suction surface, though with a clear signature in the local aero-damping, has negligible effects on the overall stability. The second part aims to examine computationally the applicability of the influence coefficient method in a linear cascade setup. The comparison between the cascade-based ICM data and a baseline “tuned cascade” shows that the differences in the sensitivity to the far-field treatment can be significant, depending on inter-blade phase angles. On the other hand, non-linearity effects closely relevant to the basic linear assumption of the ICM are shown to only have a small influence. The present results suggest that extra caution should be exercised when comparing a CFD-based tuned cascade model with a finite cascade-based ICM model, at conditions close to acoustic resonance. The resultant discrepancies may well arise from the inherently different far-field sensitivities between the two models, rather than those typical numerical and physical modeling aspects of interest (e.g., meshing, spatial and temporal discretization errors as well as turbulence modeling).

Efficient Steady and Unsteady Flow Modeling for Arbitrarily Mis-Staggered Bladerow Under Influence of Inlet Distortion

“…High-fidelity models such as LES [57] have been shown to be effective in capturing the formation of laminar separation bubble and the associated transition. In the previous computational study [58], it was shown that using the two-equation - transition correlation coupled with the RANS SST model [59] is also able to predict the formation of separation bubble. Figure 5 compares the experimental steady pressure distribution at mid-span to that predicted by the fine mesh solution with different turbulence models, confirming the previous findings.…”

Investigation of Structurally and Aerodynamically Mistuned Oscillating Cascade Using Fully Coupled Method

“…A separation bubble formation around 40 -60% chord can be observed in the experiment. Interestingly, this separation bubble can only be captured in the computation if the transitional turbulence model is used [31]. Instead, a rather smooth pressure distribution at this region is captured with the fully turbulent model.…”

“…For more details and analyses for the validation of the tuned oscillating cascade in the bending mode, particularly for the effects of laminar separation bubble and tip clearance, one is referred to Ref. [31].…”

Numerical aero-thermal study of high-pressure turbine nozzle guide vane: Effects of inflow conditions

“…Inlet endwall boundary layer thickness is another factor of uncertainty [10][11][12]. According to Denton [10], it is perhaps the most important factor and also the least likely to be known.…”

“…In addition, a variety of turbomachinery predictions has been shown to be greatly influenced by the inflow boundary conditions [10][11][12][13][14]. From the literature, the turbine vane aero-thermal performance is also affected by the inflow conditioning.…”