Unsteady Pressure Measurement on Oscillating Blade in Transonic Flow Using Fast-Response Pressure-Sensitive Paint

Watanabe, Toshinori; Azuma, Toshihiko; Uzawa, Seiji; Himeno, Takehiro; Inoue, Chihiro

doi:10.1115/1.4039180

Cited by 13 publications

(3 citation statements)

References 9 publications

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“…An annular sector cascade is sometimes used instead of the conventional linear cascade [11]. Some recent efforts are aimed to experimentally study the flutter mechanism in a transonic linear cascade [12,13].…”

Section: Introductionmentioning

confidence: 99%

“…Proposed by Hanamura et al [18], this is the most common method in getting equivalent tuned cascade data from experimental linear cascades and annular sector rigs with only the middle blade oscillating, e.g. [4,5,7,8,9,10,11,13]. The validity of the ICM has been commonly judged mainly in terms of linearity of the unsteady flow, thus the applicability of superposition.…”

Section: Introductionmentioning

confidence: 99%

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

Phan

2020

Journal of Turbomachinery

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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).

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Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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

Phan

2020

Journal of Turbomachinery

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“…Since Hanamura et al [41] proposed the Influence Coefficient Method (ICM), it has become the most common method in getting equivalent tuned cascade data from experimental linear cascades and annular sector rigs with only one blade oscillating [42][43][44][45][46][47][48][49][50][51]. The classical use of the ICM is to calculate the 1 st harmonic unsteady pressure coefficient of the reference blade 1 in a travelling wave mode by summing the unsteady pressure coefficients from the oscillating blade itself and its neighboring stationary blades, taking into account the constant inter-blade phase angle (IBPA):…”

Section: Staggering-dependence Source Term Calculationmentioning

confidence: 99%

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

Phan

2020

Volume 10A: Structures and Dynamics

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Accurate and efficient predictions of the steady and unsteady flow responses due to the blade-to-blade variation as well as due to the non-axisymmetric inlet distortion have been continually pursued. Computation of two problems concurrently has been rarely done in the past partly because of the need to perform whole annulus bladerow simulations, despite the advances in the current state-of-the-art methods with the phaseshift single passage simulations. The current work attempts to deal with this challenge by developing a new computational approach based on the principle of the multiscale method in the framework of a commercial solver (CFX). The methodology formulation relies on summation of the constituent source terms, each of which corresponds to a particular flow perturbation. The source term element corresponding to the blade-to-blade variation effect is linearly superimposed as in the classical Influence Coefficient Method. Only the relative positions between the reference blade and its neighbor matter in this method, thus enables an arbitrarily mis-staggered bladerow to be computed efficiently. In addition, the source term arisen due to the inlet distortion is calculated based on spatial Fourier transform. A key enabler is that the source term can be pre-computed using a small set of identical blade passages. The source term is then propagated to different spatial and temporal locations depending on the combination of the mis-staggering pattern and the inlet distortion. The multiscale treatment makes it possible to predict a high-resolution flow field effects on the base coarse mesh as if the fine mesh is solved, while achieving a computational gain. The source term summation method proposed in the current work has been validated using a uniformly staggered bladerow, and an arbitrarily mis-staggered bladerow in a clean inflow condition as well as that subject to an inlet distortion.

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Experimental Investigation of a Linear Cascade with Large Solidity Using Pressure Sensitive Paint and Dual-Camera System

et al. 2021

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Unsteady Pressure Measurement on Oscillating Blade in Transonic Flow Using Fast-Response Pressure-Sensitive Paint

Cited by 13 publications

References 9 publications

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

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

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

Experimental Investigation of a Linear Cascade with Large Solidity Using Pressure Sensitive Paint and Dual-Camera System

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