航空发动机燃烧室两相湍流燃烧建模与仿真

[Objective] As the energy-producing component of aeroengines, the combustor is the core area of fuel atomization, oil and gas mixing, and chemical reaction. Its design directly affects the overall performance of the engine. The structure of an aeroengine combustor is complex, allowing for a series of complicated physical and chemical processes. [Methods] The application of numerical simulation is of great significance in shortening the development cycle of the combustor while reducing test experiments and risks in design. In this paper, we conduct a bottom-up study on framework design, model integration, software development, test validation, and engineering application of the self-developed software platform. First, we design a hierarchical simulation software by analyzing the common numerical algorithm of an individual physical model and optimizing the secondary development interface of the model code. The software framework can be divided into three levels from bottom to top: unstructured grid high-performance parallel programming framework, particle-fluid computing layer, and advanced physical models and methods. The software framework has a reasonable data structure and highly scalable function interface, which guarantees the independence and high maintainability of each model and supports the R&D team in realizing the efficient integration of different types of physical models. Second, for the complex two-phase turbulent combustion process in the combustor, ten physical models suitable for simulating engine combustors, such as fuel atomization, wall oil film, evaporation, and turbulent combustion models, are integrated. Four hierarchical test cases of three-stage swirl, gas-phase swirl, simple cylinder and model combustor configurations are constructed, and the coupling consistency of multiple models is studied and improved. Based on the work related to the framework, model, and validation, a parallel adaptive unstructured grid combustor two-phase turbulent combustion numerical simulation software (CBTLES), which can run efficiently on modern mainstream high-performance computers, was developed. Finally, to test the engineering applicability of CBTLES, two-phase turbulent combustion simulation in the annular main combustor and afterburner of a large turbofan engine are conducted. [Results] The simulation results showed that: 1) thousand-core parallel efficiency reached 104.50%, while the ten thousand-core parallel efficiency reached 70.92%, indicating that CBTLES has good parallel scalability for hundreds of millions of grid-scale annular combustor cases. 2) Qualitative simulation results of unsteady two-phase turbulent combustion were consistent with physical phenomena, indicating that CBTLES has engineering coupling simulation ability with a typical two-phase physical model. 3) With typical working conditions, the quantitative errors of the total pressure recovery coefficient and outlet temperature distribution coefficient of the main combustor were 1.2% and 9.7%, respectively, while the errors of the total pressure recovery coefficient and average outlet temperature of the afterburner were 5.6% and 0.9%, respectively, revealing that CBTLES has acceptable engineering simulation accuracy. Generally, CBTLES realizes a breakthrough from 0 to 1 through framework design, model integration, software development, test verification, and engineering application in this paper. [Conclusions] The engineering simulation results of a typical annular main combustor and afterburner show that the simulation efficiency, function, and accuracy of CBTLES meet practical engineering requirements. Simultaneously, it also reveals that physical models integrated into CBTLES realize the key transformation from basic theory to engineering applications.