跨声速压气机转子多目标优化设计  

Multi-objective optimization of a transonic compressor rotor

作　　者：钟兢军[1] 高宇[1] 李晓东[1] 

机构地区：[1]大连海事大学轮机工程学院,辽宁大连116026

出　　处：《大连海事大学学报》2017年第2期89-96,共8页Journal of Dalian Maritime University

基　　金：国家自然科学基金重点资助项目(51436002);辽宁省高等学校创新团队项目(LT2015004);中央高校基本科研业务费专项资金资助项目(3132016334)

摘　　要：为提高某型跨声速压气机转子的总性能,基于全三维优化设计平台,采用人工神经网络与遗传算法相结合的方法,对一跨声速压气机转子进行三维叶型多目标优化设计,优化目标是在流量基本不变的基础上提高转子的压比和效率.结果表明,设计点时,与原型转子相比,优化方案1(opt1)效率提高0.81%,压比提高1.55%;优化方案2(opt2)效率提高0.36%,压比提高3.09%.同时,opt1与opt2的喘振裕度与原型转子相比,分别增加1.58%和0.89%.因此,减小50%叶高并增大95%叶高叶型的安装角,结合调整吸力面前、尾缘楔角可有效控制跨声速压气机转子叶片表面载荷分布,进而提高转子总性能.To improve overall performances of transonic compressor rotor,the multi-objective optimization design of the blade profile was carried out by using the combination method of artificial neural network and genetic algorithm based on full three-dimensional optimization design platform. The optimization target is to increase the pressure ratio and efficiency by keeping the rate of flow invariant fundamentally. Results show that corresponding to the design point, the efficiency and pressure ratio of opt1 increase 0. 81% and 1. 55% respectively compared with those of the original blade profile,and the efficiency and pressure ratio of opt2 increase 0. 36% and3. 09% respectively,and the stall margin of opt1 and opt2 increase 1. 58% and 0. 89% respectively. Therefore,the blade load distribution can be regulated and controlled by decreasing at 50% blade height and increasing the stagger angle at 95%blade height,and adjusting the wedge angles of leading edge or trailing edge in suction surface,in turn,which improves overall performances of rotor.

关 键 词：跨声速压气机 多目标优化 安装角 吸力面 前尾缘 楔角 叶型设计 

分 类 号：V235.1[航空宇航科学与技术—航空宇航推进理论与工程]