航空发动机燃烧室数字孪生体系关键技术

The curvilinear coordinate system’s immersion boundary method (IBM) can be used to realize high-fidelity virtual-real mapping of the real aero-engine combustor in the design stage, and retain all the geometric structure information. Based on the IBM method, large eddy simulation (LES) combined with transported probability density functional turbulent combustion model (TPDF) was used to simulate the real structure of a double-swirler combustor, a single-head model of a throughflow combustor and 1/10 model of a slinger combustor, and test the effectiveness of key technologies of the digital twin system. Compared with the prediction and experiment results, the average errors of axial, radial and tangential velocities near the outlet of the swirler of the double-swirler combustor were 15.7%, 23.8% and 15.0%, respectively. The detailed turbulent combustion fields of the single-head model of a throughflow combustor and the slinger combustor were analyzed under the unsteady state, and the average relative errors of the outlet temperature distribution were 11.66% and 17.95%, respectively. Therefore, the combustor’s digital twin system obtained based on virtual real mapping has certain effectiveness, and the proposed method has potential engineering application prospects.