Aero-thermal optimization of in-flight electro-thermal ice protection systems in transient de-icing mode

Pourbagian, Mahdi; Habashi, Wagdi G.

doi:10.1016/j.ijheatfluidflow.2015.05.012

Cited by 73 publications

(32 citation statements)

References 16 publications

(9 reference statements)

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“…The mass and energy balance equations took into account the input water caused by droplet impingement, but the water film runback mechanism was not taken into consideration. Habashi et al [18][19][20] developed a conjugate model for the in-flight deicing process. The airflow and droplet impingement were calculated as initial solutions, and the solid conduction was solved, which was coupled with a water phase transition in a loosely coupled way.…”

Section: Introductionmentioning

confidence: 99%

Numerical Simulation of Unsteady Conjugate Heat Transfer of Electrothermal Deicing Process

Lin

Shen

et al. 2018

International Journal of Aerospace Engineering

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A novel 3-D unsteady model of in-flight electrothermal deicing process is presented in this paper to simulate the conjugate mass and heat transfer phenomena of water film runback, phase change, and solid heat conduction. Mathematical models of water film runback and phase change are established and solved by means of a loosely coupled method. At the current time step, solid heat conduction, water film runback, and phase change are iteratively solved until the heat boundary condition reaches convergence, then the temperature distribution and ice shape at the moment are obtained, and the calculation of the next time step begins subsequently. A deicing process is numerically simulated using the present model following an icing tunnel experiment, and the results match well with those in the literatures, which validate the present model. Then, an in-flight deicing process is numerically studied to analyze the effect of heating sequence.

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Section: Introductionmentioning

confidence: 99%

Numerical Simulation of Unsteady Conjugate Heat Transfer of Electrothermal Deicing Process

Lin

Shen

et al. 2018

International Journal of Aerospace Engineering

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“…Deicing systems cost much less energy than anti-icing systems 7 , and are typically implemented using electrical heating. In addition, the electrical heaters of the thermal deicing systems are usually arranged inside the aircraft component skins, which results in high heating efficiency, short response time and good control performance 8 .…”

Section: Introductionmentioning

confidence: 99%

Unsteady simulation of aircraft electro-thermal deicing process with temperature-based method

Shen

Wang

Lin

et al. 2019

Proceedings of the Institution of Mechanical Engineers, Part G:

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Considering the mass and energy sources carried by the accumulated ice layer, an unsteady heat and mass transfer model of the runback water film on the deicing surface is established to simulate aircraft electro-thermal deicing process. With the extension of the freezing coefficient to the transient calculation, the coupled heat transfer of the runback water and the solid skin is solved at each time step by a temperature-based method. Unsteady numerical simulation is carried out for the electro-thermal deicing system of a NACA 0012 airfoil. The temperature variations with time are in acceptable agreement with the literature data, and the unsteady temperature-based deicing model is verified. The calculation results of temperature, runback water flux and ice thickness on the deicing surface are analyzed at different time points, and it is shown that the unsteady electro-thermal deicing model can capture the main features of the icing, ice melting and re-freezing processes in the transient deicing simulations.

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“…Many important micro-physical phenomena associated with wind turbine icing are still unclear. The previous icing physics studies are concentrated on aircraft applications [19][20][21][22] . Many special issues related to wind turbine icing have never been explored.…”

Section: Introductionmentioning

confidence: 99%

An Experimental Investigation on the Dynamic Ice Accretion Process over the Surface of a Wind Turbine Blade Model

Gao

Yang

2017

9th AIAA Atmospheric and Space Environments Conference

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An experimental study was conducted to investigate the dynamic ice accretion process over the suction-side and pressure-side surfaces of a wind turbine blade with a DU91-W2-250 airfoil profile to elucidate the impact of angle of attack (AoA) on the underlying physics of the active pitch control (APC) technique for wind turbine icing mitigation. A glaze ice condition was simulated for this experiment in the Icing Research Tunnel of Iowa State University (ISU-IRT) with an ambient temperature T∞ =-5 °C, an oncoming flow velocity U ∞ = 40 m/s, and a liquid water content (LWC) level LWC = 3.0 g/m 3. Four typical AoAs (i.e. 0 °, 5 °, 10 °, and 15 °) were selected to represent the most commonly-used operation conditions of wind turbine blades. A high-speed imaging system was utilized to quantitatively measure the transient behaviors of water runback and the dynamic ice accretion process over the blade model surface. Simultaneously, an infrared (IR) thermal imaging system was also used to provide time evolutions of surface temperature distributions during the icing process. The experimental results show that AoA can affect the dynamic ice accretion process over the turbine blade model surface significantly. The ice impacted region over the suction-side surface and pressure-side surfaces decrease and increase, respectively, as AoA increases. The temperature distributions over both sides of the test model surface varies significantly with respect to AoA. Two 'peak' regions instead of the usual one have been observed in the measured surface temperature distributions due to the surface water runback over the ice accreting blade model surface. The upstream 'peak' region appears near the LE due to the locally larger liberation of latent heat with higher water collection. The location of downstream 'peak' region varies depending on AoA. As AoA increases, the downstream 'peak' moves upward over the suction-side surface and moves further downstream over the pressure-side surface. A water/ice film stretching from the TE towards the LE has been identified. The ice accretion near the LE leads to large-scale flow separations near the TE, which is responsible for this interesting phenomenon.

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Aero-thermal optimization of in-flight electro-thermal ice protection systems in transient de-icing mode

Cited by 73 publications

References 16 publications

Numerical Simulation of Unsteady Conjugate Heat Transfer of Electrothermal Deicing Process

Numerical Simulation of Unsteady Conjugate Heat Transfer of Electrothermal Deicing Process

Unsteady simulation of aircraft electro-thermal deicing process with temperature-based method

An Experimental Investigation on the Dynamic Ice Accretion Process over the Surface of a Wind Turbine Blade Model

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