Generally, combustor and turbine components of aeroengine are designed in a relatively isolated manner and simplified boundary conditions from experiment or numerical simulation are commonly used at the interface. However, the hot gas at combustor exit is characterized by high non-uniformity of temperature, pressure, and flow distribution which may significantly affect turbine performances and reliability. Moreover, the presence of high-pressure turbine guide vanes also affects combustor flow field. The coupled simulation of combustor and turbine can describe the interaction between them more accurately. Combustor and turbine components are generally simulated with different flow solvers since they are working at different Mach number range with different flow and physical characteristics. In this work, a 3D multi-solver coupled simulation system is developed where multiple flow solvers are coupled by using two different coupling approaches. In the first approach, a 2D interface is used to connect the computational domains of combustor and turbine, the data extracted from combustor exit (including total pressure, total temperature, velocity profile and turbulent quantities) is sent to turbine guide vane inlet and the static pressure profile at combustor exit is defined by turbine. In the second approach, the computational domains have a 3D overlap region where virtual body forces are added in combustor simulation in order to enforce the 3D velocity, temperature and turbulence profiles which is provided by the turbine simulation. Moreover, data from combustor simulation is also extracted and interpolated onto the turbine inlet and vice versa in the second approach. The validation from a swirling jet case shows that the coupling system works well and the second approach provides more accurate results. Then a coupled simulation of aeroengine combustor and turbine are performed. Isolated simulation is also done for comparison. Results of these simulations are compared. It can be seen that the non- uniformity of temperature and flow distribution at combustor exit and hot streaks transport are successfully captured by the coupled simulation. The features have an important influence on the temperature distribution of turbine. Besides, the influence of turbine guide vanes on combustor flow field is mainly at the region close to combustor exit. The multi-solver coupled simulation system could be useful for designer to fully consider the interaction between combustor and turbine and gain more precise engine performance and improved turbine cooling design.
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