摘要
多级轴流压气机气动设计的核心是S2通流设计和叶片造型设计。为了提高设计效率、降低时间成本,研究开发了多级轴流压气机通流、造型一体化设计方法。通过将S2通流设计反问题与叶片造型耦合联结,一体化设计获取压气机气动流场参数和流道、叶片几何,并直接与全三维数值模拟相衔接,可快速得到基本满足目标需求的初始设计。通过一体化反演设计具有设计数据与试验结果的美国E^3十级高压压气机前六级,其设计点的流量、绝热效率误差范围均在2.5%内,具有较好的工程精度,验证了研发的多级轴流压气机通流造型一体化设计的有效性与实用性。
The core of multi-stage axial flow compressor aerodynamic design are S2 through-flow and blade design.In order to reduce its time cost and improve design efficiency,research develops a method of integrated through-flow and blade design of multi-stage axial flow compressor.Integrated design for compressor aerodynamic flow field parameters,blade geometry and connect with three-dimensional numerical simulation by coupling S2 through-flow and blade design,which can achieve target of fast initial design.Besides,by using this method to conduct inversing design six stage axial flow compressor of E3,and its resulting error of flow and adiabatic efficiency are below 2.5% compare to experimental value of E3 compressor.Result shows it has good engineering accuracy thus verifies its validity and practicality.
出处
《工程热物理学报》
EI
CAS
CSCD
北大核心
2016年第6期1218-1224,共7页
Journal of Engineering Thermophysics
基金
国家自然科学基金资助项目(No.51576007)
关键词
轴流压气机
气动设计
S2通流
叶片造型
E^3高压压气机
axial compressor
aerodynamic design
S2 through-flow
blade design
E^3 high-pressure compressor
