| Areoengine design is a complex system project, which is involved many different fields, such as thermodynamics, fluid dynamics, combustion, heat transfer, structure strength, and engine's reliability and durability. Multidisciplinary Design Optimization (MDO) is a newly engineering technology which has been the hot research direction. Thougth the engine components MDO researches have achieved some results, the overall engine MDO research is just at the initial stage. The performance calculation of the overall engine is the base of MDO. To solve the limits and low accuracy problems of 0-D calculation, a 2-D model has been developed. And then, a MDO method of overall aero engine which based on the preliminary simulation has been proposed in this thesis.The optimization procedure is setup on the MDO platform named MUDO, and the interface codes are developed. The research of the overall engine performance calculation shows that the results of CANSS is reasonable and reliable, and satisfy the engineering requirements. This calculation can capture the flow features in earoengine, and promotes the calculation from 0-D to quasi 3-D, which increased the simulation accuracy. Nevertheless, preliminary design, of which the calculation size and the time cost are much less than that of full 3-D numerical, is suitable and potential for overall engine MDO.The method of aeroengine weight calculation has been researched. The overall engine weight is estimated with the component weights, which are calculated with formulas. An overall aeroengine MDO including preliminary design model and weight estimate model is achieved.A turbofan aeroengine has been simulated with S2 calculation, and the flowpath has been parameterized. Then, MDO about components and overall aeroengine have been finished. For the guidance of the development in the next stage, this project aims at increased push with constant weight. Meanwhile, the feasibilities of the overall aeroengine S2 calcultion and its combination with weight estimate for optimization have been validated, and a new method for overall aeroengine MDO is proposed. |
