旋转冲压压缩转子试验系统通流部分数值研究

Numerical Research on Flow Passage of Ram-Rotor Test System

关键词:  旋转冲压压缩转子  试验系统  通流部分  气动性能  数值模拟

Key words:  Ram-rotor  Test system  Flow passage  Aerodynamic performance  Numerical simulation

摘要:

为了评估旋转冲压压缩转子试验系统的气动性能，采用Fluent软件对其通流部分在设计转速下的流场进行了全通道数值模拟。分析了旋转冲压压缩转子达到最高效率时，试验系统各部分的总体性能以及导叶段、旋转冲压压缩转子段和出口支板段的流动特征。计算结果表明，进口段和导叶段内气流损失较小，总压恢复系数分别为0.995和0.979，且气流在导叶内基本实现了预期的偏转和加速。旋转冲压压缩转子压比较高，单转子压比可到2.756。超声速压缩面区域不同节距方向的激波系结构有较大差异，同时存在正常反射和马赫反射现象。出口支板段存在大范围的流动分离，不利于出口气流顺畅的流出。

Abstract:

In order to evaluate the aerodynamic performance of the ram-rotor test system，FLUENT software was used to carry out numerical simulation on the flow passage of the ram-rotor test system at the design speed. Overall performance of each segment of the test system was analyzed at peak efficiency condition of the ram-rotor，and the flow characteristics of the vane，the ram-rotor and the support segments were also discussed. It has been found that the flow loss in the inlet and vane segments is low，and the total pressure recovery coefficients are 0.995 and 0.979，respectively. The flow in the vane passage is deflected and accelerated as expected. There is a high total pressure ratio of 2.756 in the ram-rotor segment. The structure of shock waves along the pitch direction is different in the zone of the supersonic compression ramp，and normal and Mach reflection of shock waves are observed at the same time. It has the large scale flow separation in the support segment，and the outflow of the test system can not benefit from this.