Abstract:
The physical and mathematical models for three-dimensional steady fluid-solid coupled heat transfer were presented for wing hot air anti-icing system. These models simulate the effects of internal and external heat transfer as well as thermal conductivity of solid structure on aircraft leading edge skin. Hybrid grid was generated for the entire computational domains. The third kind of boundary conditions was used for the present simulations. Internal and external skin temperature field for fluid-solid coupled heat transfer under dry air flight condition were solved by computational fluid dynamic method with FLUENT tool, and the calculated results were analyzed. The results indicate that heat conducting is significant along leading edge spreading and thickness direction on aluminium alloy skin, temperature distributions on the skin are uniform. When the temperature of inlet bleed air is 200℃, the maximal surface temperature of skin on anti-icing system is 101℃, the minimal surface temperature is 21℃, the maximal temperature difference between the inside and outside surface is only 4℃ for 3mm thick skin, the average temperature of exhaust is 63℃. The present method and calculated results of temperature field can provide support for the dry air flight test design of hot air anti-icing system and reasonable choosing and distributing temperature sensors.