摘要
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.
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.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2007年第8期1356-1364,共9页
Journal of Aerospace Power
关键词
数学分析
最优化
航天推进系统
高压压缩机
人工神经网络
叶栅
aerospace propulsion system
high pressure compressor
numerical optimization
blade row match
artificial neural network
