大推力并联混合动力涡扇发动机全航程综合能量管理策略设计及验证  

Design and verification of a comprehensive energy management strategy for high-thrust parallel hybrid turbofan engine during a full-range flight route

作　　者：陈佳杰 陈新民 方菁菁 王继强 张海波[4] 胡忠志 CHEN Jiajie;CHEN Xinmin;FANG Jingjing;WANG Jiqiang;ZHANG Haibo;HU Zhongzhi(Zhejiang Engineering Research Center for Special Aircraft,Ningbo Institute of Materials Technology&Engineering,Chinese Academy of Sciences,Ningbo 315201,China;Qianwan Institute of NIMTE,Ningbo 315336,China;Zhejiang Development&Planning Institute,Hangzhou 310030,China;College of Energy and Power Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China;Institute for Aero Engine,Tsinghua University,Beijing 100084,China)

机构地区：[1]中国科学院宁波材料技术与工程研究所特种飞行器浙江省工程研究中心,浙江宁波315201 [2]宁波杭州湾新材料研究院,浙江宁波315336 [3]浙江省发展规划研究院,浙江杭州310030 [4]南京航空航天大学能源与动力学院,江苏南京210016 [5]清华大学航空发动机研究院,北京100084

出　　处：《推进技术》2024年第10期1-15,共15页Journal of Propulsion Technology

基　　金：宁波市3315甬江引才项目(2022A-012-G);宁波市重大科技任务攻关项目(2022Z040)。

摘　　要：为使大推力航空并联混合动力推进系统在考虑节能减排效益的同时,充分挖掘涡轮电气化后部件的性能提升潜力,本文依托某并联混合动力齿轮传动涡扇发动机(Parallel hybrid geared turbofan,PH-GTF)推进系统概念模型,在“发动机主燃油闭环+电动力系统转矩补偿”控制结构下,针对典型飞行航程所包括的低功率工况段、起飞爬升段、巡航段、下降段,分别设计了相应的能量管理策略,并基于不同飞行工况在全航程内进行调度。通过典型飞行航线下的数字仿真及硬件在环(Hardware in the loop,HIL)仿真验证,结果表明,相较于未采用混合动力改型的基线GTF发动机,应用所设计综合全航程能量管理策略的PH-GTF推进系统,该航线下总燃油消耗量和NO_(x)排放量分别降低5.70%和10.72%,其中在低功率工况下,可变放气活门(Variable bleed valve,VBV)可以减小54.35%的排气量;在航空节能减排所重点关注的等高等速巡航段,耗油量和NO_(x)排放量分别降低18.93%和30.19%。所设计综合全航程能量管理策略兼顾了部件性能提升和节能减排效益,符合未来绿色航空推进系统的设计理念。In order to fully explore the performance improvement potential of components after turbine elec-trification while considering fuel saving and emission reduction benefits in the high-thrust parallel hybrid propul-sion system,this paper relies on the conceptual model of a parallel hybrid geared turbofan(PH-GTF)propulsion system,under the control architecture of engine fuel closed-loop control system combined with electric power sys-tem torque compensation.Corresponding energy management strategies are designed for the low-power condi-tions,take-off and climb phase,cruise phase,and descent phase included in a typical flight route,and schedul-ing is carried out throughout the full range based on different flight conditions.Through digital simulation and hardware in the loop(HIL)verification under the typical flight route,the results show that compared to the base-line GTF engine without hybrid modifications,the PH-GTF propulsion system with the designed comprehensive full-range energy management strategy reduces total fuel consumption and NOx emissions by 5.70%and 10.72%,respectively.Under low-power conditions,variable bleed valve(VBV)can reduce the exhaust air volume by 54.35%.In the cruise phase(constant altitude and speed)which is a key focus of aviation energy conservation and emission reduction,fuel consumption and NOx emissions were reduced by 18.93%and 30.19%,respective-ly.The designed comprehensive full-range energy management strategy takes into account both the engine compo-nent performance improvement and energy-saving and emission reduction benefits,which is in line with the de-sign concept of future green aviation propulsion systems.

关 键 词：并联混合动力 大推力 涡扇发动机 能量管理 硬件在环 

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]