Numerical Simulation Analysis of a Guide Vane Hot Air Anti-icing System

Wei, Dong; Zhu, Jian; Zhao, Qian

doi:10.2514/6.2011-3944

Cited by 7 publications

(4 citation statements)

References 6 publications

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“…Tests were performed under warm hold, cold hol,d and descent in-flight icing conditions with different parameters of bleed air. Dong et al [17,18] conducted experiments to investigate the performance of hotair and hot lubrication oil anti-icing systems using the YFB-02 icing wind tunnel. The computational fluid dynamics (CFD) method of simulating anti-icing performance was also developed, and the comparisons between computation results and experiment data showed that the CFD prediction of the surface temperature was satisfied.…”

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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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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“…Shires et al [7] have performed experiment with an anti-ice cascade vanes (both electro-thermal and hot air anti-icing system were tested). Dong et al have tested a sector of five guide vanes, equipped with a hot air anti-icing system [8], and more recently, an engine strut anti-icing system using hot lubricating oil [9]. Tatar et al [10] also investigated experimentally the efficiency of a hot air anti-icing system for a stator vane.…”

Section: Introductionmentioning

confidence: 99%

Experimental characterization of anti-icing system and accretion of re-emitted droplets on turbojet engine blades

Linassier

Balland

Pervier

et al. 2018

2018 Atmospheric and Space Environments Conference

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In the framework of STORM, a European project dedicated to icing physics in aircraft engines, a cascade rig representative of an anti-iced engine inlet was tested in icing conditions. This mock-up integrates two rows of vanes, the upstream one being anti-iced using an Electro-Thermal Ice Protection System (ET-IPS). Experimental tests were performed to reproduce the following phenomena: runback water and droplet re-emission from anti-iced vanes, and accretion of re-emitted droplets on downstream vanes. A complete experimental database was generated, including the characterization of ice accretion shapes, and the characterization of electro-thermal anti-icing system (power limit for apparition of the runback water or ice accretion). In the current study, these data are compared to droplet trajectory simulation and ice accretion simulation results, for validating icing tools in engine environment. Influence of one-step and multi-step approaches have been investigated.

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“…The physics behind icing problem is not well understood and the models are improved continuously in order to solve this complex problem more accurately. Significant effort is expended in the numerical simulation to predict the performance of the anti-icing system [16][17][18][19] . The temperature of anti-icing surface can be determined from the heat balance equation on the surface by considering the heat loss by convection, sensible heating of the supercooled water impinging on the surface, and heat loss by evaporation of the water film that forms on the surface.…”

Section: Introductionmentioning

confidence: 99%

Heat Transfer and Temperature Analysis of an Anti-icing System for an Aero-engine Strut under Icing Condition

Wei

Zhu

Zhou³

et al. 2012

43rd AIAA Thermophysics Conference

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Ice accretion on the inlet of an aero-engine could adversely affect the characteristics of the flow field into the engine and degrade the engine's performance. When the accrued ice sheds, the portion sucked into the engine could induce serious damages. One method to reduce hazards caused by in-flight icing is an anti-icing system that utilizes hot lubricating oil from the engine rather than utilizes the hot gas. This method not only decreases the amount of anti-icing hot air required but also cools the lubrication oil. This paper presents a computational study of the temperature distribution of an aero-engine strut under icing condition. The flow field around the strut is simulated using ANSYS FLUENT CFD code. The trajectories of the super-cooled water droplets and the local collection coefficient are calculated through the Lagrangian approach after the computation of the air flow field. The coupling effects of heat transfer and mass transfer are considered in the temperature calculation of the strut studied. The thermal model takes both the mass balance of water and the energy balance on the surface of the strut into account. The convection heat transfer coefficients on the surface of the strut are obtained through two methods: correlation equations and CFD calculations. Finally, comparisons between the computational results and the experimental data are presented. NomenclatureA = area, m 2 C D = drag coefficient D = leading edge diameter, m D r = drag force, N G v = gravity force, N I = evaporation latent heat, J/kg LWC = liquid water content, g/m 3 MVD = mean volumn diameter, µm Nu = Nusselt number P = pressure, Pa P v = saturated vapor pressure, Pa 2 Q = heat flux, W/m 2 Re = Reynolds number S = stream length T = temperature, K θ = angle degree c p = specific heat, J/(kg·K) d = droplet diameter, µm h = convective heat transfer coefficient, W/(m 2 ·K) k = conduction heat transfer coefficient, W/(m·K) m = mass, kg m & = mass flow rate, kg/s n = water droplet number r = radius, m v r = velocity vector, m/s β = local collection coefficient µ = coefficient of dynamic viscosity, N·s/m 2 ρ = density, kg/m 3 τ = time, s Subscripts S = stream length a = air d = water droplet e = external edge of boundary layer evap = evaporation ht = impingement surface area imp = droplets impingement in = inlet of control volume m = impinging location of droplet o = original location of droplet out = outlet of control volume rel = relative s = solid t = total w = water wall = solid wall ∞ = free stream

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Numerical Simulation Analysis of a Guide Vane Hot Air Anti-icing System

Cited by 7 publications

References 6 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

Experimental characterization of anti-icing system and accretion of re-emitted droplets on turbojet engine blades

Heat Transfer and Temperature Analysis of an Anti-icing System for an Aero-engine Strut under Icing Condition

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