Combustion and Particulate I/SVOC Characteristics of an Aero-engine Combustor with Dual-Stage under Operational Power and Injection Pressure

Abstract

The combustion and particulate intermediate-volatile/semi-volatile organic compound (I/SVOC) emission characteristics of a technology of low emission stirred swirl aero-engine combustor, which was operated under dual combustion stages of diffusion and premixed-dominant combustion have been investigated. The operational conditions of the combustor were combustor power (7% - 100%) and injection pressure (IP, 1.5 - 6.0 MPa). Initially, the ignition and extinction boundary regions were identified, and within the ignition region, the emitted I/SVOCs were comprehensively resolved via a two-dimensional gas chromatography-time of flight mass spectrometer (GC×GC-ToFMS). It is found that I/SVOCs were remarkable under diffusion combustion, and reduced significantly by 61% under premixed-dominant combustion (at 3.0 MPa IP). Besides, I/SVOCs were suppressed prominently by 49% as IP increased from 1.5 MPa to 6.0 MPa (at 30% combustor power). Based on the Response Surface Method (RSM), a model has been established to simulate the particulate I/SVOCs. The simulation model reveals that high Power-IP (100% power, 6 MPa IP) could reduce I/SVOCs maximally by 84%, 78% and 56% for n-alkanes, cycloalkanes and PAHs, respectively in comparison with low Power-IP (30% power, 1.5 MPa IP). The essence of the findings reveals that domination of premixed combustion with promotional atomization inhibits aviation-emitted organic particles effectively.