高空低雷诺数风扇/增压级气动设计  

Aerodynamic Design of Fan-Booster under Condition of High Altitude and Low Reynolds Number

作　　者：杨加寿 冀国锋 YANG Jia-shou;JI Guo-feng(AECC Guiyang Aero-Engine Research Institute,Guiyang 550081,China)

机构地区：[1]中国航发贵阳发动机设计研究所,贵州贵阳550081

出　　处：《推进技术》2020年第10期2190-2196,共7页Journal of Propulsion Technology

摘　　要：为发展一型适用于高空低雷诺数流动的风扇/增压级部件,解决高空长航时无人机动力对部件的技术需求,针对高空低雷诺数下的风扇/增压级进行了气动设计,设计过程包含了一维热力计算、S2通流设计、叶片造型设计和三维数值计算分析。经过多轮设计迭代后,得到了适用于高空低雷诺数条件下的最优叶型。三维数值计算结果表明:风扇/增压级的内、外涵性能都达到了设计指标的要求,且在高空低雷诺数下有较高的稳定裕度。与现有发动机风扇部件性能进行对比得出:新设计的风扇/增压级具有较好的高空工作能力,可以满足总体对风扇/增压级的性能需求。In order to develop a type of fan/booster suitable for high-altitude and low Reynolds number flow to solve the problem of HALE UAV power demand,the aerodynamic design of fan/booster working under the condition of high altitude and low Reynolds number is performed.The design process includes 1 D thermodynamic calculation,S2 through flow design,blade profiling design and 3 D numerical calculation.After the design iteration is carried out for several times,the optimum blade profile suitable for high altitude and low Reynolds condition is acquired.The results of 3 D numerical calculation indicate that the core and bypass performances of fan/booster accord with the requirements of design targets,and have a high stability margin at high altitude and low Reynolds number.Compared with the performance of current engine fan component,the newly designed fan/booster has better ability for operation at high altitude and can satisfy the performance requirements addressed by overall engine.

关 键 词：低雷诺数 风扇 压气机 气动设计 叶片造型 数值模拟 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]