Thereorical Analysis, Experimental Study Of Scramjet Combustor Operation Process

The performance analysis and evaluation method, schematic design and optimization, ignition and combustion performance and their relative conditions, internal flow field and its characteristics of kerosene fueled scramjet combustor are studied detailedly and comprehensively by means of theoretical analysis, experimental investigation and numerical simulation. Many results are obtained.The methodology for scramjet combustor performance analysis and evaluation is build up. A computer program for two phases, multi species, chemical reacting flow analysis and computation in scramjet combustor is worked out. This provides an effective means for rapid performance analysis and design optimization of scramjet combustor.Based on the concept of penetration depth of fuel jet, the concept of relative penetration depth of fuel jet is presented. This concept is applied successfully in the ignition and combustion performance analysis of the scramjet model.Three hundred and thirty eight scramjet model experiments in same simulation flying conditions were conducted in the conditions of different ignition method, different structural and working parameters. The ignition and combustion performance of kerosene fueled scramjet combustor are studied detailedly and comprehensively. The kerosene was ignited by the oblique shockwave induced by the leading edge of the full height strut and stable combustion was sustained. But too thick strut can make the combustor choke. Combination use of the oblique Shockwave induced by the leading edge of the half height strut and hydrogen pilot flame can also ignite the kerosene and hold the combustion stably. Because of the relative penetration depth of the fuel jet, the ignition performance of hydrogen pilot flame has relations with the combustor scale. There is an energy threshold value beyond which kerosene can be ignited by the igniters. The equivalent fuel/air ratio range in which the kerosene can combust stably without choking has close relations with the ignition method, the structural parameters of the combustor, etc. Many parameters, such as the fuel jet pressure drop, the equivalent fuel/air ratio, the position of the fuel injectors, the relative penetration depth of the fuel jet, the ignition method, the structural parameters of the combustor, the structural parameters of the cavity, and so on, do have influences on the combustion performance of the scramjet combustor.