航空并联混合动力专用涡扇发动机快速设计方法  

Rapid design of dedicated turbofan engine for parallel hybrid propulsion system

作　　者：刘光璧 王步宇[1] 王向阳[1] 帅石金[1] LIU Guangbi;WANG Buyu;WANG Xiangyang;SHUAI Shijin(Institute for Aero Engine,Tsinghua University,Beijing 100084,China)

机构地区：[1]清华大学航空发动机研究院,北京100084

出　　处：《航空动力学报》2023年第8期1909-1925,共17页Journal of Aerospace Power

基　　金：航空科学基金(2020Z39058001)。

摘　　要：为解决航空并联混合动力系统直接使用传统涡扇发动机时存在的发动机效率下降与低压压气机喘振问题,提出了一种通过质量流量预测确定涵道比的并联混合动力专用涡扇发动机快速设计方法,使用PROOSIS搭建了并联混合动力涡扇发动机模型,对发动机设计结果进行了性能评估与能量利用分析。研究表明,在与基准发动机相同的涡轮前总温限制下,设计结果能够满足推力需求。与在并联混合动力系统中使用基准发动机相比,使用设计的专用发动机时的油耗、能耗、低压压气机防喘振性能更优。混合度越高,使用专用发动机产生的性能提升越大。由于能量利用历程不同,发动机外涵道电能利用率远高于内涵道电能利用率和燃油利用率,这是并联混合动力涡扇发动机节能的根本原因。In order to avoid the surge of low pressure compressor and decrease of efficiency when using directly conventional turbofan engine in the parallel hybrid propulsion system,a rapid design method of dedicated turbofan engine for parallel hybrid propulsion system was proposed based on the designed bypass ratio from prediction of flow rate.A parallel hybrid turbofan engine model was developed using PROOSIS to study the performance and energy utilization of the designed dedicated engines.It was found that under the constraint on turbine inlet temperature the same as the baseline engine,the dedicated engine can provide the needed thrust.Compared with the baseline engine in the parallel hybrid propulsion system,the anti-surge performance of low pressure compressor,fuel and energy consumption of the dedicated engine were better.As degree of hybridization increased,the benefits from using dedicated engine increased.Because of the difference in the energy utilization process,the energy utilization efficiency of electric power supplied to bypass was much higher than that of electric power supplied to core and fuel,serving as a fundamental reason of saving energy when using parallel hybrid turbofan engine.

关 键 词：并联混合动力系统 涡扇发动机 快速设计 能量利用 稳态性能 

分 类 号：V235.13[航空宇航科学与技术—航空宇航推进理论与工程]