为验证民用大涵道比涡扇发动机对《航空发动机适航规定》CCAR33.76吸鸟适航条款的适用性，针对吸鸟条款中的中鸟附加完整性子条款开展数值仿真研究。基于风扇叶片鸟撞过程动力学仿真结果及鸟撞前后风扇特性数值计算结果，以某型发动机为例建立吸鸟过程动态性能仿真模型，完成了发动机从吸鸟开始到最终稳定的动态过程仿真，获得了吸鸟过程及最终稳定后的性能变化情况。结果表明：吸鸟后发动机性能急剧变化的主要因素是风扇叶片的塑性形变，通过起飞状态发动机吸鸟前后稳态节流特性对比，起飞推力下降约8%，满足持续的功率或推力损失不超过25％的条款要求；随着转速下降，风扇外涵喘振的风险极高，需改进设计保证吸鸟后风扇外涵仍具有足够的裕度；吸鸟前后，涡轮进口温度及发动机排气温度均下降，不存在超温风险。

In order to verify the applicability of the civil turbofan engine with large bypass ratio to the requirements of the CCAR33.76 bird ingestion of the Airworthiness Regulations for Aeroengine,the numerical simulation study on the additional integrity subclause of the medium bird for the bird ingestion clause was performed.Based on the dynamic simulation results of the bird strike process of the fan blades and the numerical calculation results of the fan characteristics before and after the bird strike,the dynamic performance simulation model of the bird ingestion process was established with a certain engine as an example,the dynamic process simulation of the engine from the beginning of the bird ingestion to the final stability was completed,so as to obtain the performance changing situations in the bird ingestion process and after the final stability.The results show that the main factor for the sharp change in the performance of the engine after the bird ingestion is the plastic deformation of the fan blades.By comparing the steadystate throttling characteristics of the engine in the takeoff state before and after the bird ingestion,the takeoff thrust is reduced by about 8%,which meets that the continuous power or thrust loss is not more than 25% in this clause.As the speed decreases,the risk of external fan culvert surge is extremely high,the design needs to be improved to ensure that the external fan culvert still has sufficient stall margin after the bird ingestion.Before and after the bird ingestion,the turbine inlet temperature and engine exhaust gas temperature both drop and do not have the risk of over temperature.

V231.3

国家科技重大专项（2017-Ⅷ-0003-0114）