单外涵变循环发动机变几何特性仿真  

Simulation of Variable Geometry Characteristics of Single Bypass Variable Cycle Engine

作　　者：牟园伟 王奉明 朱大明 MU Yuan-wei;WANG Feng-ming;ZHU Da-ming(Aero Engine Academy of China,Beijing 101304,China;Advanced Jet Propulsion Innovation Center,Beijing 101304,China)

机构地区：[1]中国航空发动机研究院,北京101304 [2]先进航空动力创新工作站,北京101304

出　　处：《航空发动机》2024年第2期52-57,共6页Aeroengine

基　　金：先进航空动力创新工作站项目(HKCX2020-02-004)资助。

摘　　要：为了研究单外涵变循环发动机变几何性能收益,建立了一种单外涵变循环发动机总体性能仿真模型,并通过算例验证了仿真模型的计算精度。根据不同飞行状态的发动机控制规律和最优控制目标,模拟生成3种变几何方案最佳变几何参数以及最佳节流特性和高度-速度特性。结果表明:在设定的控制规律下,相对发动机常规变几何方案(方案1),尾喷管、混合器与低压涡轮导向器可调的变几何方案(方案3)使发动机地面节流状态耗油率降低1.7%~3.0%,超声速巡航推力增大14%~29%,亚声速巡航耗油率降低0.9%~3.1%,在3种变几何方案中性能收益最大;尾喷管与混合器可调的变几何方案(方案2)使发动机地面节流状态耗油率降低1.2%~2.2%,超声速巡航推力增大3%~17%,亚声速巡航耗油率降低0.9%~1.2%,在3种变几何方案中性能收益居中。发动机变几何方案的选择应综合考虑结构复杂度、可靠性、质量等方面的代价与基于特定任务需求的总体性能收益的平衡。To investigate the performance gain of the single bypass variable cycle engine,we established a simulation model and veri⁃fied its computational accuracy through examples.The simulation and generation of the best variable geometry parameters,throttling characteristics,and altitude-velocity characteristics for the three variable geometry schemes are based on the engine control laws and optimal control objectives for different flight states.The study indicates that Scheme 3,which employs a variable geometry scheme with adjustable tail nozzle,mixer,and low-pressure turbine guide,outperforms Scheme 1,the conventional engine variable geometry scheme.Scheme 3 reduces fuel consumption rate by 1.7%to 3.0%in ground throttling state,increases supersonic cruise thrust by 14%to 29%,and reduces fuel consumption rate by 0.9%to 3.1%in subsonic cruise.This represents the largest performance gain among the three variable geometry schemes.Scheme 2,the variable geometry scheme with an adjustable tail nozzle and mixer,can reduce fuel consumption rate by 1.2%to 2.2%in ground throttling state,increase supersonic cruise thrust by 3%to 17%,and reduce subsonic cruise fuel consumption rate by 0.9%to 1.2%.Among the three variable geometry schemes,Scheme 2 exhibits intermediate performance gains.When selecting engine geometry options,it is important to consider the balance between the costs of structural complexity,reliability,and mass,and the overall performance gains based on specific mission requirements.

关 键 词：变循环发动机 变几何 单外涵 仿真模型 耗油率 

分 类 号：V235.1[航空宇航科学与技术—航空宇航推进理论与工程]