MODELE DE FLUX DE REFROIDISSEMENT DE ZONE PRIMAIRE DE COMBUSTOR

摘要

A gas turbine engine combustor has a shell defining a combustion chamber having a primary zone and a dilution zone downstream of the primary zone. The shell has an outer skin and an inner skin defining an air gap therebetween. The inner skin in the upstream portion of the primary zone is free from effusion holes and has heat transfer increasing projecting from a back side to the air gap. Effusion holes in the inner skin have only been reduced to the end of the primary phase of the process that could potentially interfere with the combustion process.