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Research Papers

Thermal Boundary Layer Response to Periodic Fluctuations for Turbulent Flow

[+] Author and Article Information
J. Saavedra, G. Paniagua

Mechanical Engineering,
Purdue University,
West Lafayette, IN 47907;
von Karman Institute for Fluid Mechanics,
Rhode-Saint-Genèse B-1640, Belgium

O. Chazot

von Karman Institute for Fluid Mechanics,
Rhode-Saint-Genèse B-1640, Belgium

Manuscript received July 9, 2018; final manuscript received July 18, 2018; published online October 4, 2018. Assoc. Editor: Riccardo Da Soghe.

J. Eng. Gas Turbines Power 141(3), 031009 (Oct 04, 2018) (9 pages) Paper No: GTP-18-1470; doi: 10.1115/1.4041138 History: Received July 09, 2018; Revised July 18, 2018

The detailed characterization of the thermal boundary layer under periodic fluctuations is vital to improve the performance of cooled turbine airfoils, as well as to assess noise thermal and structural fatigue. In the present contribution, we performed detailed unsteady Reynolds-averaged Navier–Stokes (URANS) simulations to investigate wall heat flux response to periodic flow velocity fluctuations over a flat plate. We also investigated the boundary layer response to sudden flow acceleration including periodic flow perturbations, caused by inlet total pressure variations. During a flow acceleration phase, the boundary layer is first stretched, resulting in an increase of the wall shear stress. Later on, due to the viscous diffusion, the low momentum flow adjusts to the new free stream conditions. The behavior of the boundary layer at low frequency is similar to the response to an individual deceleration followed by one acceleration. However, at higher frequencies, the mean flow topology is completely altered. One would expect that higher acceleration rates would cause a further stretching of the boundary layer that should cause even greater wall shear stresses and heat fluxes. However, we observed the opposite; the amplitude of the skin friction coefficient is abated, while the peak level is a full order of magnitude smaller than at low frequency.

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Figures

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Fig. 1

(a) Numerical domain for flow acceleration research, (b) inlet total pressure profile for flow acceleration analysis, and (c) inlet total pressure profile for periodic perturbation analysis

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Fig. 2

(a) Axial velocity at (0.4, 0.07) for different mesh resolutions and (b) grid convergence indicator

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Fig. 3

(a) Free stream axial velocity evolution and (b) wall shear stress evolution: during a sudden flow acceleration

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Fig. 4

(a) Free stream axial velocity, (b) skin friction coefficient, and (c) heat flux: evolution during a flow acceleration after characteristics delay correction

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Fig. 5

Momentum boundary layer profile at different acceleration phases for both steady and transient evaluation

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Fig. 6

Thermal boundary layer profile at different acceleration phases for both steady and transient evaluation

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Fig. 7

(a) Raw cd signal, (b) cd representation of two consecutive periods after convergence, and (c) cross correlation factor of two consecutive periods after convergence

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Fig. 8

Flow and wall fluxes response to periodic excitations at x/L = 0.5: (a) axial free stream velocity, (b) static pressure, (c) skin friction coefficient, (d) heat transfer coefficient, and (e) acceleration parameter

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Fig. 9

Static pressure contour along the domain: (a) 5 Hz excitation and (b) 100 Hz excitation

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Fig. 10

Acceleration parameter effect on the aero-thermal boundary layer: (a) acceleration parameter, (b) skin friction, and (c) heat flux

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Fig. 11

(a) Numerical domain for validation, (b) velocity magnitude contour on the modeled test section, and (c) skin friction coefficient over test article

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Fig. 12

Boundary layer displacement thickness at x/L = 0.5 for various excitation frequencies

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Fig. 13

Momentum boundary layer profiles during the excitation period, for Strouhal numbers 0.0045–0.909 (5, 10, 20, 50, 100 Hz) and steady conditions

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Fig. 14

Thermal boundary layer profiles during the excitation period, for Strouhal numbers 0.0045–0.909 (5, 10, 20, 50, 100 Hz) and steady conditions

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