涡扇发动机带动力数值模拟  

Numerical Simulation of Turbofan Engine with Power

作　　者：郝海兵[1] 李蔷薇 梁益华[1] 颜洪[1] 

机构地区：[1]中航工业西安航空计算技术研究所,陕西西安710068 [2]中国东方航空西北分公司,陕西西安712035

出　　处：《航空计算技术》2013年第6期13-17,共5页Aeronautical Computing Technique

基　　金：国家自然科学基金项目资助(50976017);国家863计划项目资助(2012AA01A304)

摘　　要：基于等熵流动原理,通过在排气口处设定总温比/总压比,进气口处设定质量流量,提出了一种新型的发动机进排气边界条件。通过与N-S方程耦合求解,数值模拟了轴对称超高涵道比涡扇模拟器CURF和单独涡轮动力模拟器进排气流场,数值结果表明:计算结果和实验值吻合较好,验证了提出的发动机进排气边界条件的正确性,同时也验证了涡扇发动机带动力流场计算方法的可靠性。To model the aerodynamic effects of turbofan engine properly, a new approach of engine inlet and exhaust boundary conditions is constructed and presented based on the isentropic flow principle, in which the total pressure ratio and total temperature ratio at exhaust plane and the mass flow at inlet are specified. Incorporating the new boundary conditions into around an axisymmetric ultra- high bypass ratio turbofan were simulated. Compared with the experiment data, the the solving of Navier- Stokes equations, the flow simulator CURF and a turbine powered simulator numerical results show that the engine inlet and exhaust flowfields are accurately simulated by the newly presented boundary conditions. The reliability of the numerical method simulating turbofan engine with power is verified as well.

关 键 词：涡扇发动机计算模型 边界条件 涡轮动力模拟器 N-S方程 

分 类 号：V211[航空宇航科学与技术—航空宇航推进理论与工程]