Numerical Simulation of Surface Heat Transfer from an Array of Hot Air Jets

Saeed, Farooq; Al-Garni, Ahmad

doi:10.2514/6.2007-4287

Cited by 6 publications

(4 citation statements)

References 22 publications

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“…Using the velocity field, the energy Eq. (11) and the turbulence model equations (12) and (13) are then solved sequentially. The linearized equations are solved using an algebraic multi-grid method.…”

Section: B Ansys Cfxmentioning

confidence: 99%

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Numerical Validation of CHT3D/CFX in Anti-/de-Icing Piccolo System

Hannat

Morency

2012

4th AIAA Atmospheric and Space Environments Conference

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Anti-/de-icing CHT method based on ANSYS-CFX flow solver and FENSAP-ICE software is presented. The ANSYS-CFX flow solver is used as the flow solver module with the , SST turbulence model. DROP3D is used as the droplet impingement module. ICE3D is used as the ice accretion and water film runback module. CHT3D/CFX is used for the thermal coupling of all modules. Before solving for the temperature distribution in a 3D anti-icing system geometry based on a piccolo tube with three jet rows, a test case consisting of a two stream parallel gas to gas micro heat exchangers is used to validate the CHT3D/CFX procedure. For the anti-icing system in wet air mode temperature results at corresponding experimental locations are presented and compared to results from literature. Nomenclatureheat at constant pressure for water c = chord d = nozzle diameter e = internal energy Fr = Froud number GCI = Grid Convergence Index g = gravity (m s -1 ) h = enthalpy h f = thickness of the film h tot = total enthalpy I = turbulent intensity K = droplet inertia parameter k = turbulence kinetic energy k f = fluid thermal conductivity LWC = liquid water content MVD = median volumetric diametrer ! !"# = mass flow at jet inlet Nu = local Nusselt number Nu = average Nusselt number Pr = Prandtl number p = pressure Q S = conduction heat flux from the wall in the normal direction Q w = wall heat flux 2 q = heat flux Re = jet Reynolds number Re D = droplet Reynolds number r = airfoil radius at leading edge s = curvilinear distance T = temperature T b= bulk temperature T wall = wall temperature T 0.air = free stream temperature T 0 , jet = total temperature at jet inlet t = time U = mean velocity u = velocity components in x direction u a = dimensionless air velocity u d = dimensionless droplet velocity over a small fluid element around the location x at time t u f = velocity of the water in the film V air = free stream velocity = relaxation parameter = mean value of the nondimensional water volume fraction ε = relative error µ = laminar dynamic viscosity µ T = turbulent viscosity = normal vector ρ = air density ω = specific dissipation

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Section: B Ansys Cfxmentioning

confidence: 99%

“…ANSYS-CFX 12.1 uses a collocated finite volume method to solve Eqs (9), (10) (11), (12)and (13). The gas law Eq.…”

Section: B Ansys Cfxmentioning

confidence: 99%

Numerical Validation of CHT3D/CFX in Anti-/de-Icing Piccolo System

Hannat

Morency

2012

4th AIAA Atmospheric and Space Environments Conference

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“…Their correlations for the average and maximum Nusselt numbers with relation to different nozzle-to-nozzle spacing, nozzle-to-surface height, and hot air jet Mach number are derived. Saeed et al [9] employed commercial CFD software, FLUENT, to study the effects of different hot jet arrangements on heat transfer. They concluded the etched surface or inner liner yields better surface heat transfer than the others so that such design patterns were favorable recommended.…”

Section: Introductionmentioning

confidence: 99%

Critical Design Points for the Wing Anti-Icing System

Zhu

Han

Hongliang

et al. 2013

51st AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

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The design parameters for the wing anti-icing system (WAIS) are determined with the flight conditions and atmospheric and meteorological conditions. To meet such a variety of conditions, the worst conditions are generally considered for the WAIS design. In this paper an approach is proposed to determine the design parameters for the WAIS, ie critical design points (CDP). In the framework of the Eulerian method, both of the air flow field and droplet impingement behavior are obtained by numerically solving two sets of Navier-Stokes equations. As the result, the heat flux requested for dry surface conditions is estimated, on the other hand, the heat flux supplied for icing prevention by the piccolo tube system (PTS) can be calculated based on the first law of thermodynamics. Then the distributions of connective heat transfer coefficients and droplet impinging mass flux along the wingspan are predicted.

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“…The maximum Nusselt number occurred at the jet stagnation point, and the distance between adjacent jet holes had negligible effect on it. In 2008, Saeed [20] conducted a simulation study to further understand the jet impingement heat transfer performance employing a piccolo tube with single one row and two rows of staggered jet holes impinging on the internal surfaces of a typical aircraft wing/slat. The 3-D distributions of the Nusselt number and heat transfer coefficient on the target surface were illustrated, and the results showed that the jet impingement heat transfer performance for the piccolo tube with single one row and two rows of 20 degree staggered jet holes was better than that with 4 two rows of 10 degree staggered jet holes.…”

Section: Introductionmentioning

confidence: 99%

Jet impingement heat transfer on a concave surface in a wing leading edge: Experimental study and correlation development

Peng

Lin

et al. 2016

Experimental Thermal and Fluid Science

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Extensive experimental studies of the heat transfer characteristics of jet impingement on a variable-curvature concave surface in a wing leading edge were conducted for aircraft anti-icing applications. The experiments were performed on a piccolo tube with three rows of aligned jet holes over a wide range of parameters: the jet Reynolds number (Rej) from 50,000 to 90,000, the relative tube-to-surface distance (H/d) from 1.74 to 20.0, the jet impingement angle ( ) from 66° to 90°, and the relative chordwise arc length in the jet impingement zone (r/d) from 13.2 to 34.8. The experimental results indicated that the heat transfer performance at the stagnation point was enhanced with increasing Rej and , and an optimal H/d existed to achieve the best heat transfer performance at the stagnation point. It was found that the attenuation coefficient curve of the jet impingement heat transfer in the chordwise direction exhibited an approximate bell shape with the peak located at the stagnation point, affected only by r/d in the peak zone. In the non-peak zone, however it was affected significantly by a variety of factors including Rej, H/d and r/d. Experimental data-based correlations of the Nusselt number at the stagnation point and the distribution of the attenuation coefficient in the chordwise direction were developed and validated, which can be used to predict the performance of a wing leading edge anti-icing system.

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Numerical Simulation of Surface Heat Transfer from an Array of Hot Air Jets

Cited by 6 publications

References 22 publications

Numerical Validation of CHT3D/CFX in Anti-/de-Icing Piccolo System

Numerical Validation of CHT3D/CFX in Anti-/de-Icing Piccolo System

Critical Design Points for the Wing Anti-Icing System

Jet impingement heat transfer on a concave surface in a wing leading edge: Experimental study and correlation development

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