Optimization on turbofan engine cycle parameter based on improved differential evolution algorithm

摘要

In this paper, a two-spool mixed turbofan is considered. The turbofan is one of the research hotspots for military and civil aircraft power device, which shows outstanding performance advantages. Compared to the turbojet, turbofan is more efficient. For getting the performance of turbofan, the model for engine performance simulation is researched. The method for engine performance simulation and the cycle parameters for turbofan are discussed. For obtaining the optimal design of turbofan, suitable optimization method is required. Unfortunately, the optimization of the turbofan engine design is a non-linear non-differentiable problem, which makes it difficult to solve by conventional deterministic optimization method. In order to solve this problem, the differential evolution (DE) algorithm is considered. To overcome the original algorithm DE limitations, an improved DE algorithm with modifying mutation operator is proposed by this paper. The turbofan optimization problem is solved by employing the improved DE algorithm.