Computational Methodology for Bleed Air Ice Protection System Parametric Analysis

Domingos, Rodrigo; Papadakis, Michael; Zamora, Alonso

doi:10.2514/6.2010-7834

Cited by 18 publications

(19 citation statements)

References 33 publications

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“…Currently, almost all the thermal anti-icing studies and software packages, including LEWICE [16]，FENSAP-ICE [17]，ONERA [18]， CANICE [19] and ICECREMO [20], use this method. The iterative procedure of the conjugate heat transfer is expensive, as each domain (especially the fluid domain) could take a considerable amount of time to converge [21,22]. Therefore, the external air flow is usually decoupled from the conjugate heat transfer solution of the anti-icing system in traditional loose-coupling methods.…”

Section: Introductionmentioning

confidence: 99%

Numerical simulation of aircraft thermal anti-icing system based on a tight-coupling method

Lin

Shen

et al. 2020

International Journal of Heat and Mass Transfer

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Section: Introductionmentioning

confidence: 99%

Numerical simulation of aircraft thermal anti-icing system based on a tight-coupling method

Lin

Shen

et al. 2020

International Journal of Heat and Mass Transfer

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“…LEWICE [16] assumes that water solidification occurs over a small artificial temperature range instead of at the freezing point, and then defines a freezing coefficient related with the temperature range between water and ice phases to calculate the heat load. Using the temperature-based method with this assumption, Domingos [28] simulated a hot-air anti-icing system, and Shen [29] calculated the temperature variations of an electro-thermal de-icing system. However, the influence of the freezing point extension on thermal anti-icing simulations has not been analyzed, and the value of the artificial temperature range has not been given in those articles, either.…”

Section: Introductionmentioning

confidence: 99%

Study on Loose-Coupling Methods for Aircraft Thermal Anti-Icing System

et al. 2020

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To simulate aircraft thermal anti-icing systems and solve the conjugate heat transfer of air-droplet flow and solid skin, the heat and mass transfer model of the runback water on the anti-icing surface was combined with the heat conduction equation of the skin by loosely coupled methods. According to the boundary conditions used for the runback water conservation equations, two loose-coupling methods for the heat exchange between the runback water and the solid skin were developed based on surface heat flow and surface temperature, respectively. The anti-icing and ice accretion results of a NACA 0012 electro-thermal anti-icing system were obtained by the two loose-coupling methods. The heat flow-based method directly solves the thermodynamic model of the runback water without any extra assumptions, but the convergence rate is relatively slow. On the other hand, the temperature-based method achieves higher calculation speed, but the freezing point is extended to an artificial temperature range between water and ice phases. When the value of the artificial temperature range is small, the results obtained by the temperature-based method are consistent with those of the heat flow-based method, indicating that the effect of freezing point extension can be ignored for thermal anti-icing simulation. Furthermore, the solutions of the two methods are in acceptable and comparable agreement with the experimental and simulative results in the literature, confirming their feasibility and effectiveness. In addition, it is found that the ice thicknesses and ice shapes rise obviously near the runback water limits as a result of the transverse heat conduction of the solid skin.

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“…15 computed leading edge skin temperature and runback ice location. They developed a numerical tool that combines data from a commercial CFD solver for external flow field and heat transfer correlation for internal flow heat transfer.…”

Section: Introductionmentioning

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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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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Computational Methodology for Bleed Air Ice Protection System Parametric Analysis

Cited by 18 publications

References 33 publications

Numerical simulation of aircraft thermal anti-icing system based on a tight-coupling method

Numerical simulation of aircraft thermal anti-icing system based on a tight-coupling method

Study on Loose-Coupling Methods for Aircraft Thermal Anti-Icing System

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

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