A Visual Study of Turbine Blade Pressure-Side Boundary Layers

Han, L. S.; Cox, W. R.

doi:10.1115/1.3227397

Cited by 16 publications

(2 citation statements)

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“…This difference between model predictions results in an increase in vortex shedding period as shown in Table 5. In agreement with previous experimental work, 21,22 both modeling approaches show the pressure side shear layer to dominate the vortex shedding process. As described by Han and Cox this is due to the rapid expansion around the pressure side trailing edge, resulting in vortex pairs that have been highlighted in red.…”

Section: Resultssupporting

confidence: 91%

A characterization of unsteady effects for transonic turbine airfoil limit loading

Owen,

Taremi,

Uddin

2023

Proceedings of the Institution of Mechanical Engineers, Part A:

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To better understand the effect of vortex shedding on the nature of the trailing edge shock system during airfoil limit loading a computational fluid dynamic investigation was performed for a transonic turbine airfoil at sublimit, limit and supercritical conditions. Four modeling strategies were employed: steady state RANS, unsteady RANS, DDES, and turbulence model free. The influence of transient modeling approaches on the predicted mass-flow averaged total pressure loss coefficient, mass-flow averaged flow angles, and on the limit loading pressure ratio were found to be insignificant with the exception of the URANS model during critical loading. It was found that the URANS modeling approach failed to predict the transition from near trailing edge dominated vortex formation to base pressure vortex formation resulting in a drastic rise in predicted total pressure loss. Surface isentropic Mach distributions were predicted similarly for all modeling strategies, with the exception of the trailing edge base pressure region and points of shock impingement along the suction surface. A detailed review of the boundary layer states at the trailing edge was performed. It was found that all of the modeling approaches predicted laminar boundary layer profiles along the pressure surface trailing edge and turbulent profiles along the suction surface. The predicted base pressure distributions were also reviewed, showing the base pressure to decrease with increasing pressure ratio. The unsteady simulation approaches consistently predicted lower average surface pressures than the steady state RANS simulations. Qualitative images of the numerical Schlieren contours were presented and reviewed showing large differences in the prediction of vortex shape, size, and subsequent shock influence.

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Section: Resultssupporting

confidence: 91%

A characterization of unsteady effects for transonic turbine airfoil limit loading

Owen,

Taremi,

Uddin

2023

Proceedings of the Institution of Mechanical Engineers, Part A:

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“…Although much data are already available on the wakes produced by smooth bodies, [1][2][3][4][5][6][7][8][9][10][11][12] almost no papers exist which provide information on the influences of body roughness on wake flow characteristics, especially with augmented levels of mainstream turbulence. To remedy this deficiency, the present study considers the effects of surface roughness on the wake characteristics of a symmetric airfoil, operating in a compressible, high-speed environment, with different levels of freestream turbulence.…”

Section: Introductionmentioning

confidence: 99%

Effects of surface roughness and freestream turbulence on the wake turbulence structure of a symmetric airfoil

2004

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The effects of surface roughness on the wake characteristics of a simulated turbine airfoil, operating in a compressible, high-speed environment, are studied at different freestream turbulence levels. The effects of these parameters on wake distributions of mean velocity, turbulence intensity, and turbulence length scale, as well as on power spectral density profiles and vortex shedding frequencies are quantified one chord length downstream of airfoil. All profile quantities broaden considerably, with lower peak values, as either the level of surface roughness of the turbulence intensity increases. Non-dimensional vortex shedding frequencies also decrease as either the level of surface roughness or the turbulence intensity increases.

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Analyses of Urans and Les Capabilities to Predict Vortex Shedding for Rods and Turbines

Ferrand

Boudet

Caro

et al.

Unsteady Aerodynamics, Aeroacoustics and Aeroelasticity of Turbomachines

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A Visual Study of Turbine Blade Pressure-Side Boundary Layers

Cited by 16 publications

References 0 publications

A characterization of unsteady effects for transonic turbine airfoil limit loading

A characterization of unsteady effects for transonic turbine airfoil limit loading

Effects of surface roughness and freestream turbulence on the wake turbulence structure of a symmetric airfoil

Analyses of Urans and Les Capabilities to Predict Vortex Shedding for Rods and Turbines

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