Large Engines Combustor Demonstrator - Technology Demonstration - Investigation of Second Advanced Cooling Mixing Concept

Abstract

This report describes the experimental results of the investigation of an atmospheric rich burn quick quench lean burn pilot stage for a radially staged aeroengine combustor. The central sector of a rectangular five nozzle RQL combustor with impingement cooling in the primary and film cooling in the secondary zone has been studied. In this combustion concept secondary air is brought into the combustor through one row of secondary air inlet holes on each side of the liner, enveloped by primary zone cooling air. Velocities, temperatures and exhaust concentrations have been measured from the end of the primary zone to the defined combustor end. The results allow to describe the suitability of the combustion process.