环绕式涡桨进气道主流道设计及优化方法  

Design and Optimization Method of Sprue of Surrounding Turboprop Inlet

作　　者：张宜琳 钟易成[1] ZHANG Yilin;ZHONG Yicheng(College of Energy and Power Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China)

机构地区：[1]南京航空航天大学能源与动力学院,江苏南京210016

出　　处：《机械制造与自动化》2024年第1期73-77,共5页Machine Building & Automation

摘　　要：为研究环绕式涡桨进气道主流道设计方法,使用环形截面设计方法进行参数化设计,使用型线方程和3次B样条曲线构建进气道气动型面。使用数值模拟的方法,开展不同上、下型线参数方程和圆心扩展角变化规律对进气道性能影响的研究,通过调整参数得到进气道优化后的构型。结果表明:优化后得到的进气道模型相较于初始模型总压恢复系数提高0.13%,总压畸变降低8.4%。To study the design method of the sprue of surrounding turboprop inlet,the annular section design method is applied to carry out the parametric design,and the profile equation and the cubic B-spline curve are used to construct the aerodynamic profile of the inlet.By numerical simulation,the influence of different upper and lower profile line parameter equations and the variation law of the expansion angle of the circle center on the performance of the intake port is studied,and the optimized configuration of the intake port is obtained by adjusting the parameters.The results show that compared with the initial model,the total pressure recovery coefficient of the intake port model obtained after optimization is increased by 0.13%,and the total pressure distortion is reduced by 8.4%.

关 键 词：涡桨发动机 进气道 参数化 优化设计 总压畸变 

分 类 号：V211.48[航空宇航科学与技术—航空宇航推进理论与工程]