摘要
为评估起飞飞机发动机喷流的影响范围及程度,分析后侧穿越方案可行性,在SA湍流模型基础上,结合脱体涡模拟(DES)方法,数值模拟后侧穿越方式下的起飞飞机发动机喷流影响距离;选取热喷状态下的高亚音速喷管模型进行数值模拟,对比模拟结果与文献参考值,验证该方法的正确性和有效性;在此基础上,结合B737-800机型发动机实际边界条件,数值模拟发动机喷流效应,得出B737-800机型发动机喷流的影响距离,并与飞机特性手册对比,验证其准确性。结果表明:用改进的DES方法结合SA模型数值模拟B737-800发动机,可得出喷流在速度44、22及16 m/s时的影响距离,DES方法可较好模拟发动机喷流效应。
In order to evaluate influence range and degree of take-off aircraft engine jet and analyze feasibility of rear traverse scheme,influence distance of take-off aircraft engine jet under rear traverse mode was numerically simulated based on SA turbulence model combined with DES method.A high subsonic nozzle model was selected for numerical simulation,and simulation results were compared with reference values in literature to verify correctness and effectiveness of method.On this basis,combined with actual boundary conditions of B737-800 engine,numerical simulation of jet effect of engine was carried out,and influence distance of jet of B737-800 engine was obtained,and accuracy was verified by comparing with aircraft characteristic manual.The results show that influence distance of jet flow at 44,22 and 16 m/s can be obtained by numerical simulation of B737-800 engine with improved DES method combined with SA model.
作者
何昕
胡登峰
刘成
马义龙
HE Xin;HU Dengfeng;LIU Cheng;MA Yilong(College of Air Traffic Management,Civil Aviation Flight University of China,Guanghan Sichuan 618307,China)
出处
《中国安全科学学报》
CAS
CSCD
北大核心
2021年第4期81-87,共7页
China Safety Science Journal
基金
民航局民航安全能力建设资金支持研究项目(TM2018-3-1/2)
中国民用航空飞行学院研究生创新项目(X2018-30)
中国民用航空飞行学院面上项目(J2020-066)。
