基于CFD/CSD的TRRE排气系统气-热耦合分析

Fluid-thermal Coupling Analysis Based on CFD/CSD of TRRE Exhaust System

为准确预示壁面温度分布规律,建立TRRE喷管模型。基于MPCCI的气-热耦合数值模拟方法耦合流场求解器FLUENT和结构场求解器ABAQUS进行非稳态的气-热耦合数值计算。计算结果表明:对于TRRE喷管而言,为满足全速域飞行能力,某些工况不可避免产生流动分离或回流区。大部分喷管壁面温度在1 000 K以上,低速通道喉道与下唇板等位置为局部高温区,高速通道在马赫数为3工况下温度已经达到1 800 K,在马赫数为6、巡航40 s之后最高温度达到2 200 K。

To predict the temperature distribution of wall of exhaust system of combined cycle engine accurately, the TRRE exhaust system model was established. The fluid-thermal coupling numerical simulation method based on MPCCI was used to couple the flow field solver FLUENT and the structure solver ABAQUS for the unsteady fluid-thermal coupling numerical simulation. The results show that for TRRE nozzle, it is inevitable to generate flow separation or backflow area in order to meet the need of wide range of flight capability. The temperatures of most areas of the nozzle wall are above 1 000 K, of which low-speed flow path throat and lower lip plate are locally high, the high-speed flowpath is up to 1 800 K at Ma=3, and the highest reaches 2 200 K after cruising for 40 s at Ma=6.