Aircraft Radial Engine CFD Cooling Model

摘要

The article presents convective heat transfer phenomenon by analytically and empirically taken data and CFD based model analysis. 1000 hp ASz-62IR aircraft radial engine is the object of research. This engine is being continuously operated on M18 Dromader and AN-2 aircraft. To recount heat oriented phenomena a three-dimensional CFD model was developed that accounts circumfluent flow around cylinder and cylinder head engine surfaces. The geometry includes M18 Dromader frontal airframe elements to account their influence on cooling air flow. The simulation has been conducted as a steady-state flow. Geometry and setup specific swirls and backflows were observed that increase cylinder and cylinder head rear side heat transfer coefficients. Flow along cooling fins was analysed, connecting their heat transfer coefficient dependency. Results show that local air velocity has big influence on heat flux passed by fin walls. Additionally fin performance has been calculated in means of effectiveness and efficiency. Model verification base on engine's inner walls heat transfer coefficients comparison with various empirical models that link different engines sizes and types heat transfer trends. The following models were presented: Eichberg's, Hohenberg's, Sitkei's. Essential physical gas parameters required by those models were calculated with aid of 0/1D engine cycle computer simulation.