跨音速
计算流体力学
空气动力学
转子(电动)
气体压缩机
刀(考古)
轴流压缩机
航空航天工程
前沿
计算机科学
机械
机械工程
材料科学
结构工程
工程类
物理
作者
Yanhui Duan,Zhaolin Fan,Wenhua Wu,Ti Chen
出处
期刊:International journal of turbo & jet-engines
[De Gruyter]
日期:2018-12-22
卷期号:39 (3): 251-263
被引量:1
标识
DOI:10.1515/tjj-2018-0013
摘要
Abstract In this paper, global optimization design of a transonic compressor 3D blade (Rotor 37) has been carried out by a self-developed aerodynamic shape optimization (ASO) platform based on improved parallel synchronous particle swarm optimization (PSPSO). To improve the performance of PSPSO, coefficient of variation (COV) based attenuation method with new parameters is proposed and then validated by optimization tests. Flow field of blade is calculated by an in-house computational fluid dynamic (CFD) code called PMB3D-Turbo, which is validated by Rotor 37. Choosing Rotor 37 as the case, optimization object is to maximize the peak adiabatic efficiency, meanwhile constraining mass flow and total pressure ratio. The solutions show that, the ASO platform is effective to transonic compressor blade and variations of thickness distribution near the trailing edge can help improve the adiabatic efficiency of a transonic compressor blade.
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