摘要
通过受力分析和热力过程分析建立了部件级升力风扇系统性能计算模型;分析了设计参数对性能的影响,并据此提出了升力风扇系统的初步设计方法;通过理论推导共同工作方程和数值计算共同工作线,分析了升力风扇工作线的特征以及各参数对工作线的影响;计算了升力风扇系统的高度速度和升力调节特性,并提出了升力调节的多参数联合控制规律。结果表明:性能计算模型的计算结果与CFD模拟结果趋势一致;提高设计流量和压比均可提高升力,但高压比设计会导致升力效率降低;随转速降低工作线逐渐从换算流量与压比的幂函数方程分散为一簇与马赫数相关的曲线,并且稳态与动态的工作线基本一致;多参数联合控制规律可以调节升力风扇升力并保持转速和裕度不变。
Through force analysis and thermodynamic process analysis,a component-level performance calculation model for the lift fan system was established.The impact of design parameters on performance was analyzed,and based on this,a preliminary design method for the lift fan system was proposed.By deriving the common working equations and calculating the common operating lines through numerical methods,the characteristics of the lift fan operating lines and the influences of various parameters on these lines were examined.The altitude-speed characteristics and lift adjustment characteristics of the lift fan system were calculated,and a multi-parameter joint control law for lift adjustment was proposed.The results showed that the performance calculation model’s results were consistent with the trends of CFD simulation results;increasing the design flow rate and pressure ratio can enhance the lift,but a high pressure ratio design may lead to lower lift efficiency.As the rotational speed decreased,the working line gradually dispersed from a power function of converted flow rate and pressure ratio into a cluster of curves related to Mach number,with the steady-state and dynamic operating lines being essentially consistent.The multi-parameter joint control law can adjust the lift of the lift fan system while maintaining constant rotational speed and margin.
作者
江天牧
张晓博
王占学
刘永泉
宋伟锋
JIANG Tianmu;ZHANG Xiaobo;WANG Zhanxue;LIU Yongquan;SONG Weifeng(School of Power and Energy,Northwestern Polytechnical University,Xi’an 710129,China;Shenyang Engine Research Institute,Aero Engine Corporation of China,Shenyang 110015,China)
出处
《航空动力学报》
北大核心
2025年第12期390-405,共16页
Journal of Aerospace Power
基金
国家自然科学基金(52076180)
国家科技重大专项(J2019-Ⅰ-0021-0020)
航空发动机及燃气轮机基础科学中心项目(P2022-B-Ⅰ-005-001)
中央高校基本科研业务费专项资金资助。
