CFD-Based Optimization of Electro-Thermal Wing Ice Protection Systems in De-Icing Mode

Abstract

Even if electro-thermal ice protection systems consume less energy operating in de-icing mode than in anti-icing mode, they still need to be optimized for energy usage. This paper defines suitable design variables, objective functions and constraints for such optimization. A derivative-free technique is used to carry out the optimization process, which normally needs a large number of unsteady conjugate heat transfer simulations. To avoid such prohibitive computations, reduced-order modeling (ROM) is used to construct a simplified low-dimensional model at each time step of the simulation. The approach is illustrated through test cases, showing its benefits in bringing energy and safety considerations together in designing de-icing systems. Nomenclature ice C = specific heat capacity of ice w C = specific heat capacity of water E   = power density cycle E = total heating energy c h = convective heat transfer coefficient f h = water film thickness k = dimension of design space evap L = latent heat of evaporation fusion L = latent heat of fusion subl L = latent heat of sublimation LWC = liquid water content evap m  = mass transfer rate by evaporation ice m  = mass transfer rate by ice accretion MVD = mean volumetric diameter  = POD basis function  = POD basis coefficient M = number of modes used by POD N = number of snapshots IPS Q  = Conductive heat transfer rate by IPS T = surface temperature target T = target surface temperature , d T  = far-field droplet temperature max,ice T = maximum ice thickness max, , ice cycle T = maximum ice thickness in one cycle d u = droplets velocity f u = mean water film velocity V = snapshot solution U  = free-stream velocity  = solid emissivity w  = density of water

Numerical Simulation of Unsteady Conjugate Heat Transfer of Electrothermal Deicing Process

“…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.…”

Constrained problem formulations for power optimization of aircraft electro-thermal anti-icing systems

“…Clean Sky, an aeronautical research program in Europe, has recently launched a project on the combination of smart coatings with electro-thermal systems to minimize the runback ice over natural laminar flow wings' surfaces. There are also a number of studies focused on the parametric analysis (Pourbagian and Habashi 2012) and on the optimization of electro-thermal systems in anti-icing (Pourbagian and Habashi 2013c) and de-icing (Pourbagian and Habashi 2013a) modes. More recently, the authors of the present article performed a research work (Pourbagian and Habashi 2013b) on the optimization of electro-thermal anti-icing systems.…”

Hybrid System Combining Ice-Phobic Coating and Electrothermal Heating for Wing Ice Protection

“…Hot-air anti-icing systems, often called bleed air systems, supply compressed, high temperature air from the engines to the leading edge of a wing through a tube distributed inside the wing [1][2][3]. With advances in technology, an electrical heater mat embedded underneath the leading edge of the wing was also adopted into aircrafts such as the Boeing787 [4,5]. Although the potential risk of in-flight icing is limited to take-off and landing, the huge energy consumption of thermal IPS is still a major challenge in the design of aircraft.…”