Experimental Investigation of Supersonic Combustion of Liquid Hydrocarbon Fuel Using Barbotage in the Aeroramp Configuration at M=2.5

摘要

Results of investigations of combustion of liquid hydrocarbon fuel jets aerated by air in a supersonic flow in the two-dimensional diverging-area supersonic combustor are presented. Direct-connect combustor tests were conducted at the combustor entrance Mach number M=2.5 and total temperature in the range of Tt=1635-1742K. The liquid hydrocarbon fuel supply into the combustor was executed through the modified (in comparison with the baseline) aeroramp configurations: (1) installation of baseline aeroramps at the upper and bottom walls of the combustor, (2) combined fuel feed through injector nozzles of aeroramps separately of air and of fuel aerated by air, (3) injectors with the different from baseline aeroramps angles of fuel injection and geometry nozzles. The results obtained with the modified aeroramp configurations are superior to earlier ones obtained with baseline aeroramp configuration.