高超声速涡轮发动机多级压气机性能优化

Performance Optimization of Multistage Axial Flow Compressor for Hypersonic Turbine Engine

为了满足某高超声速涡轮发动机巡航工况(Ma=3.2)性能要求,在某8级轴流压气机方案基础上,针对压气机在该工况对应转速(相对换算转速0.748)下流通能力不足问题进行设计优化。通过创建多级压气机1维分析设计平台,采用试验设计方法分析并确定了对压气机低转速性能影响较大的关键参数,基于模拟退火寻优算法完成对多级压气机气动布局的重构;通过采用宽范围低损失多段圆弧中弧线设计、高流通转子叶型设计、低转速可调静子安装角优化及各级攻角匹配优化等措施,完成了8级压气机方案的改进设计。结果表明:在巡航工况(Ma=3.2)下,8级压气机效率和喘振裕度分别提高了0.7%和17.4%,验证了多级压气机设计优化方法的有效性,可为高超声速涡轮发动机压缩部件设计和研究提供参考。

In order to meet the cruise condition(Ma=3.2)performance requirements of a hypersonic turbine engine,on the basis of an eight-stage axial flow compressor,design optimization was carried out to solve the problem of insufficient flow capacity for the compressor at corresponding speed(corrected speed:0.748)condition. By creating a one-dimensional analysis and design platform for multistage compressors,key parameters that mostly influence the compressor low speed performance were identified using Design of Experiment,and the aerodynamic layout of multistage compressors was reconstructed based on Adaptive Simulated Annealing algorithm. The improved design of the eight-stage compressor was completed by adopting measures such as multi-segment arc camber line design featuring wide range and low loss,high throughflow rotor blade profile design,low speed variable stators stagger angle optimization and angle of attack stage matching optimization,etc. The results showed that under cruise condition(Ma=3.2),the efficiency and surge margin of the eight-stage compressor were increased by 0.7% and 17.4% respectively,which verified the effectiveness of the multistage compressor design optimization method,which could provide a reference for the design and development of hypersonic turbine engine compression system.