轴扇转换式发动机最优转换点串行优化设计方法  

Serial optimization design method for optimal transfer point of a turboshaft turbofan conversion engine

作　　者：纪创 汪勇 王召广 宋劼 张海波[1] JI Chuang;WANG Yong;WANG Zhaoguang;SONG Jie;ZHANG Haibo(College of Energy and Power Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China;AECC Hunan Aviation Powerplant Research Institute,Zhuzhou 412002,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 [2]中国航发湖南动力机械研究所,湖南株洲412002

出　　处：《推进技术》2025年第4期254-266,共13页Journal of Propulsion Technology

基　　金：中央高校基本科研业务费专项资金(NT2023004);国家自然科学基金(52202474);先进航空动力创新工作站项目(HKCX2022-01-026-03);中国博士后科学基金(2023M731655);南京航空航天大学前瞻布局科研专项(1002-ILA22037-1A22);南京航空航天大学研究生科研与实践创新计划项目(xcxjh20230203)。

摘　　要：为满足停转式飞行器垂直起降与高速巡航时不同的动力需求,发动机需要在涡轴和涡扇工作模式之间进行转换。本文提出模式转换点串行优化方法,以实现轴扇转换式发动机最优模式切换。提出了一种带有核心机放气阀门轴扇转换式发动机方案,解决了涡轴模式低功率输出时,风扇和核心机流量不平衡的问题,并基于部件法建立了其气动热力学模型,稳态仿真验证了该方案的可行性;结合停转式飞行器的推力谱,提出了最优转换点串行优化设计方法,构建了综合考虑平稳切换与发动机切换后加速裕度最大的动态变维数、变目标数值最优化问题,确定了模式转换时最优的飞行高度、前飞速度、低压涡轮转速以及几何可调机构输入集合。结果表明:最优的模式转换可调机构组合为内涵道尾喷管加动力涡轮导向器,相对于调节前,该组合可使转换后的核心机相对转速降低2.5%以上。In order to meet the different power requirements of stalling aircraft in vertical take-off and land-ing and high-speed cruise,the engine needs to switch between turboshaft and turbofan operating modes.In this paper,a serial optimization method of mode switching points is proposed to realize the optimal mode switching of turboshaft turbofan conversion engines.An turboshaft turbofan conversion engine scheme with core bleed valve is proposed to solve the problem of unbalanced flow between fan and core engine at low power output in turboshaft mode.The aerodynamic thermodynamic model is established based on component method,and the feasibility of the scheme is verified by steady-state simulation.Combined with the thrust spectrum of the stalling aircraft,a se-rial optimization design method for the optimal conversion point was proposed,and the dynamic variable dimen-sion and variable target numerical optimization problem with the maximum acceleration margin after smooth switching and engine switching was constructed.The optimal flight altitude,forward flight speed,low pressure turbine speed and geometrically adjustable mechanism input set were determined during mode switching.The re-sults show that the optimal combination of mode conversion adjustable mechanism is the inner nozzle and power turbine guide vane,which can reduce the relative speed of the converted core engine by more than 2.5%.

关 键 词：轴扇转换式发动机 垂直起降飞行器 核心机放气阀门 部件级模型 最优转换点 串行优化 

分 类 号：V231.1[航空宇航科学与技术—航空宇航推进理论与工程]