Numerical investigation on intersecting-grids composite cooling structure with internal network channels

Abstract

As the Mach number and range of aerial vehicles increases, the heat protection of the combustion chamber has been a more and more important issue. Besides developing heat-tolerant materials and new combustion chamber cooling techniques, the development of advanced cooling technology is also a significant way to the thermal protection of combustion chambers, such as film cooling, intersecting-grids cooling configuration with internal network channels, laminate cooling and the combination of thermal barrier and film cooling. The internal flow condition and cooling features of the intersecting-grids cooling structure that can be applied in the combustion chambers and turbine vanes and blades of modern gas turbine engines is investigated numerically in the paper, to get knowledge of the cooling features of such structure and discuss the feasibility of applying it in cooling systems of aero-engines.