AECSC-IBM 航空发动机燃烧室数值模拟软件研发与检验

To meet the needs of high-fidelity numerical simulation of aero-engine combustors, the AECSC-IBM software was developed based on the immersion boundary method (IBM) and the large-eddy simulation-transported probability density function combustion model (LES-TPDF). The original geometric structure of the combustor was mapped with grid markers. The simulation accuracy of turbulent flow and combustion was verified by a simulation example of a twin-swirl combustor and Sandia jet flame. In the simulation of twin cyclone combustors, the average errors of axial,radial and tangential velocities at the outlet of the swirler were 15.7%, 23.8%, and 15.0%, respectively. The average relative errors of temperature and fuel mass fraction for flame-E, flame-F were 14.69% and 5.22%, 14.18% and 5.54%, respectively. Furthermore, AECSC-IBM software was applied to a single head combustor of a real structure, and the root mean square error of the simulated exit temperature was 11.66% compared with the experimental data. Example tests showed that AECSC-IBM software can map geometric models quickly and accurately, reduce the workload of complex geometry high-quality mesh generation greatly, and simulate the two-phase turbulent combustion phenomenon in the aero-engine combustion chamber efficiently and accurately. The simulation results can provide a reference for combustion field data in combustion chamber refinement research and development,presenting practical engineering value.