Optimization via FENSAP-ICE of Aircraft Hot-Air Anti-Icing Systems

Pellissier, Mathieu; Habashi, Wagdi G.; Pueyo, Alberto

doi:10.2514/1.c031095

Cited by 69 publications

(28 citation statements)

References 37 publications

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“…The computation results show that the CFD method is useful, but the empirical correlations are not accurate for the computations of internal flow heat transter and heat conduction through the metal skin. Pellissier et al [38] presented an optimization method for hot-air anti-icing systems. The external and internal airflows were computed using a finite-element N-S code.…”

mentioning

confidence: 99%

Thermal Analysis and Testing of Nonrotating Cone with Hot-Air Anti-Icing System

Wei

Zhu

Zheng

et al. 2015

Journal of Propulsion and Power

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A hot-air film-heating method designed for the anti-icing system of a small aeroengine cone is studied as well as an experimental study on its performance. Experiments are conducted under different icing conditions and hot air parameters in an icing wind tunnel, using a full-scale experimental cone model of a small aeroengine. The temperature distributions on the cone surface are measured by thermocouples. Experiment results show that the hot-air film antiicing method is effective for the cone leading edge. Also presented is a numerical simulation of the temperature distribution of the aeroengine cone under icing condition. The flowfield around the cone is obtained by computationalfluid-dynamics code. The trajectories of supercooled water droplets and the collection efficiency are calculated by the Lagrangian approach. The coupling effects of heat transfer and mass transfer are considered in the temperature computation of the cone. The thermal analysis model considers the mass balance of water and energy balance on the surface of the cone. The simulation results are compared to the experiment measurements. The characteristics of the hot-air film-heating anti-icing method are also discussed.

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confidence: 99%

Thermal Analysis and Testing of Nonrotating Cone with Hot-Air Anti-Icing System

Wei

Zhu

Zheng

et al. 2015

Journal of Propulsion and Power

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“…There are only a few studies available on optimization of anti-icing systems, mostly focusing on hot-air systems. They include sensitivity analysis of a hot-air system to geometrical and operational parameters, 7 , optimization of a hot-air system by a two-dimensional model, 8 , and optimization of a hot-air system by a three-dimensional model for the internal flow, 9 . Recently, the optimization of an electro-thermal anti-icing system has also been studied, 10 .…”

Section: Introductionmentioning

confidence: 99%

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

Pourbagian

Habashi

2013

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

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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

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“…Pellissier et al [8] presented a methodology for optimizing a hot-air anti-icing system using a single objective function based on three geometric parameters, namely piccolo tube position, tilt angle and spacing between jets. The internal flow local convection coefficient was deduced from the correlation of Goldstein et al [9].…”

Section: Introductionmentioning

confidence: 99%

NUMERICAL STUDY OF A HOT-AIR-BASED AIRCRAFT WING ANTI-ICING SYSTEM USING THE BOX-BEHNKEN DoE APPROACH

Hannat

Morency

Decoster

2013

Transactions of the Canadian Society for Mechanical Engineering

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This article proposes the use of the Box-Behnken design of experiment (DoE) methodology to study an aircraft anti-icing system. The anti-icing system consisted of a piccolo tube with round apertures for producing air jets inside a wing. Mass flow, jet to wall distance, and jet impact angle were varied, starting from an initial design, in order to maximize heat transfer effectiveness. A conjugate heat transfer procedure from commercial CFD software was used to solve for cold air external flow, compressible internal flow, and thermal conduction in the airfoil skin. The DoE methodology was validated using a single impinging jet. A quadratic model of the heat transfer effectiveness of the anti-icing system was then built using the methodology and the maximal value was sought.

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Optimization via FENSAP-ICE of Aircraft Hot-Air Anti-Icing Systems

Cited by 69 publications

References 37 publications

Thermal Analysis and Testing of Nonrotating Cone with Hot-Air Anti-Icing System

Thermal Analysis and Testing of Nonrotating Cone with Hot-Air Anti-Icing System

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

NUMERICAL STUDY OF A HOT-AIR-BASED AIRCRAFT WING ANTI-ICING SYSTEM USING THE BOX-BEHNKEN DoE APPROACH

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