发动机零部件稳态应力计算的状态函数法

An opti mization process is used to redesign blades of a high-pressure compressor.An artificial neural network (ANN) method is coupled to Navier-Stokes solvers and is applied to three different redesigns.A newrotor blade of a transonic compressor is designed by modifying thick, stacking line andinlet angle using a 3Dapproach, with a significant efficiencyi mprovement at the design point.The off-design behavior of this new compressor is also checked afterwards, which shows that the whole performance of the inlet stage is improved over a wide range of mass flow.The losses are reduced, proving the good performance of the opti mum.The whole results indicate that the opti mization method can find i mproved design and can be integrated in a design procedure. 

Numerical analysis and optimization of the inlet stage of a multi-stage high pressure compressor

An optimization process is used to redesign blades of a high-pressure compressor. An artificial neural network (ANN) method is coupled to Navier-Stokes solvers and is applied to three different redesigns. A new rotor blade of a transonic compressor is designed by modifying thick, stacking line and inlet angle using a 3D approach, with a significant efficiency improvement at the design point. The off-design behavior of this new compressor is also checked afterwards, which shows that the whole performance of the inlet stage is improved over a wide range of mass flow. The losses are reduced, proving the good performance of the optimum. The whole results indicate that the optimization method can find improved design and can be integrated in a design procedure.