基于通流方法的某涡喷发动机整机数值仿真

采用轴对称方法对带有黏性力的三维Euler方程组进行降维，利用时间推进方法求解，得到适用于航空发动机整机计算的准三维数值仿真软件，并对某涡喷发动机整机进行设计点和非设计点数值模拟。首先，对地面静止状态节流特性进行研究，将计算结果与试验数据对比可知：推力的最大相对误差为-5.1%，单位燃油消耗率的最大相对误差为+4.8%，相对转速为95%时，单位燃油消耗率最低；其次，获取了飞行马赫数为0.7工况下的高度特性以及飞行高度为3 km工况下的速度特性，将计算结果与设计参数对比可知：对于高度特性，推力的最大相对误差为-4.61%，单位燃油消耗率的最大相对误差为+5%，对于速度特性，推力的最大相对误差为-5.83%，单位燃油消耗率的最大相对误差为+5.92%；再次，分别对压气机/涡轮进行部件模拟，预测了发动机的共同工作线；最后，对发动机设计工况下的流场以及气动参数的展向分布进行了分析。

Overall simulation of a turbojet engine based on throughflow method

Based on the axisymmetric method, three-dimensional Euler equations with viscous force are turned into two-dimensional problems. The problems are solved using time-marching method, and the obtained software can be applied to the overall simulation of aircraft engine. By means of this tool, a turbojet engine on design point as well as off-design point is simulated. First, the throttle characteristics on the ground are firstly studied and are compared with the experimental data. The results reveal that the maximum error for thrust is -5.1% and that of specific fuel consumption is +4.8%. The specific fuel consumption is the smallest at 95% rotational speed. Second, altitude characteristic at flighting Mach number 0.7 and velocity characteristic on the height of 3 km are obtained through this method. The comparison between the designed value and the computation results show that, for altitude characteristic, the maximum errors of thrust and specific fuel consumption are -4.61% and +5%. For velocity characteristic, the maximum errors of both parameters are -5.83% and +5.92%. Third, Co-operating line of the engine is acquired through simulations of compressor and turbine individually. At last, flow field and spanwise distribution of aerodynamic parameters of the engine on design point are analyzed.