Towards an Analytical Model for Film Cooling Prediction using Integral Turbulent Boundary layer

The objective of this work is to develop deep theoretical methods that are based on the solution of theintegral boundary layer equations for investigating film cooling in liquid rocket engine. The integralmodel assumes that heat is transferred from hot free stream gas to the liquid film both by convectionand radiation. The mass is transferred to the free srteam gas by the well-known blowing process.Downstream of the liquid film, the gas effectiveness is obtained by solving boundary layer integralequations. It incorporates a differential model for calorimeter mixing between liquid vapors in theboundary layer with the free stream gas entrained in the boundary layer. Comparisons with existingtheoretical and experimental results indicate the film coating trends were well predicted by the presentintegral model proposed by us.

کلیدواژه ها:

FilmCoolingAnalyticalHeat TransferRocketModel