Experimental Study on Icing and Anti-Icing Characteristics of Engine Inlet Guide Vanes

Abstract

Icing and anti-icing characteristics of engine inlet guide vanes are studied in this paper. Experiments are carried out in an icing wind tunnel under different icing conditions. The tests are performed at a freestream velocity of 85 m∕s, an inlet angle of attack of 0 deg, and a freestream static temperature in the range of −8 ∼ −20°C. The icing environment parameters include a mean volume diameter of 20 μm, liquid water content in the range of 0.5 to 2.0 g∕m 3 . The experiment is performed on full-scale inlet guide vanes. The temperature distributions on the guide vane surface are measured by thermocouples. The leading-edge ice shapes of inlet guide vanes are compared under different icing conditions. The effects of freestream static temperature, liquid water content, and the mass flow rate of anti-icing hot air on the performance of the anti-icing system are presented and analyzed. Nomenclature A = area, m 2 c p = specific heat, J∕kg · K d = droplet diameter, μm h = convective heat transfer coefficient, W∕m 2 · K I = evaporation latent heat, J∕kg _ m = mass flow rate, kg∕s P = pressure, Pa P v = saturated vapor pressure, Pa Q = heat flux, W∕m 2 T = temperature,°C v = velocity, m∕s β = local collection efficiency ρ = density, kg∕m 3 Subscripts air = freestream air d = water droplet e = boundary-layer edge evap = evaporation ha = hot air imp = droplets impingement w = water

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“…That work includes the water droplets behavior and impingement study [26]- [29], which would show the water droplets trajectory and impingement behavior of super-cooled water droplets when impinging onto the model. In addition to that, others were interested in the dynamic ice accretion and shedding process of aero-engine components [4], [8], [30]- [33], which would provide a better understanding of the icing physics pertinent to aeroengine icing. Besides, the quantification of ice structure and mass also attracts the researchers' interests since the shape and mass of ice accreted on the blades are of major interest in CFD code verification and validation [30], [34], [35].…”

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