Research On Program Architecture Of Multi-level Of Complexity Analysis For Aero-engine Performance Simulation

The aero-engine performance simulation could forecast engine performance; reduce many large-scale hardware tests and provide the data reference for designers in the early design. The aero-engine performance simulation has become the critical technology in aero-engine design. Multi-fidelity and multidisciplinary have been the latest trend of aero-engine performance simulation. In this paper, a method of multi-fidelity was presented allowing more accurate prediction of the aero-engine performance and capturing the phenomenon that affects system attributes. The contents of this dissertation are as follows:(1) In order to obtain numerical solution of balancing technique on computer, Quasi-Newton method based on Broyden's principle was used to solve a system of nonlinear equations in the aero-engine performance simulation. This method is presented allowing calculating Jacobin matrixes directly after the first iteration. So, it could improve the speed of the simulation. Compared with Newton method, this method could meet the requirement of the same precision with less computing time.(2) A method is presented allowing the design optimization and presenting an overview of the integration and design optimization problem of aero-engine, In order to complete the generalized Aero-engine simulation program on iSIGHT platform, generalized modular components programs and the data exchange standards have been used. This proposed method was applied to the aero-engine performance simulation. Compared with original parameters, it has been proved that the method could obtain the optimal designs.(3) A method is presented integrating multi-level of complexity analysis techniques (Zooming technology) that capture the appropriate physics of nozzle at the 3-D state for engine systems, In order to develop the platform of multi-fidelity simulation program, 0-D engine performance simulation program and 3-D nozzle CFD software are integrated into iSIGHT platform. By means of alternating computation of program between 0-D and 3-D, the models and areas of the nozzle and mixer were adjusted automatically. The problem that the flow matches between aero-engine and nozzle in the performance simulation was solved. The thrust...