摘要
以等熵流动原理为出发点,结合发动机短舱入口、出口及远场特征边界条件,建立了一种新的涡扇发动机动力特性计算模型。在基于非结构网格的并行计算软件中实现了模型,对轴对称超高涵道比涡扇模型(CRUF)、轴对称涡轮动力模型(TPS)以及某型民用飞机整机带发动机模型进排气流场进行了数值模拟,计算结果与传统的发动机动力特性模型计算结果以及实验数据进行比较,三者吻合较好,从而验证了构造的涡扇发动机动力特性计算模型的正确性、可靠性以及工程实用性。
Based on the isentropic flow principle, a new numerical turbofan engine model was constructed by introducing farfield characteristic boundary condition and engine inlet/exhaust boundary conditions, in which the total pressure ratio and total temperature ratio at exhaust plane and the mass flow at inlet are specified. The new simulation model was implemented in our in- house unstructured/hybrid grid based parallel CFD Solver, the flow around an axisymmetric ultra- high bypass ratio turbofan simulator CRUF, a turbine powered simulator （TPS） and a typical civil aircraft with turbofan engine were simulated. Com- pared the numerical results with the experiment data and the references, show that the engine inlet and exhaust flowfields are accurately simulated by the newly presented model. The validity and reliability of the new method simulating turbofan engine with power is verified as well.
作者
谭伟伟
颜洪
郝海兵
TAN Wei- wei YAN Hong HAO Hai- bing(Xi＇an Aeronautics Computing Technique Research Institute,A VIC, Xi＇an 710068, China)
出处
《航空计算技术》
2016年第6期60-63,共4页
Aeronautical Computing Technique
基金
国家某重点专项项目资助(MJ-2015-F-010)
航空科学基金项目资助(2015ZA31002)
