摘要
针对一并联式涡轮基组合循环（TBCC）发动机进排气系统的气动方案，对其从涡轮向冲压模态转换过程中的典型工作点上的流场进行了数值模拟。结果显示：模态转换中涡轮发动机进气道的流量系数逐渐下降，反压承受能力逐渐减弱，冲压发动机进气道的流量系数逐渐增加。模态转换中，涡轮发动机喷管在不同落压比（NPR=20～80）下均无明显流动分离现象；冲压发动机喷管分离区逐渐减小，且随着落压比的增加分离程度逐渐减弱。
According to an over-under turbine based combined cycle （TBCC） engine air inlet and exhaust systems solution, typical operating points of the flow field from turbine mode to scramjet mode were numeri-cally studied. The calculating results show that turbine engine inlet flow coefficient is gradually decreased during mode transition, and the ability to withstand back pressure is gradually weakened, however, scramjet inlet flow coefficient is gradually increased. Under different pressure ratio（ =20~80）, the turbine engine nozzle had no obvious flow separation phenomenon during mode transition, but the scramjet nozzle separa-tion zone decreased, and the degree of separation gradually weakened as the pressure ratio decreased.
出处
《燃气涡轮试验与研究》
北大核心
2013年第6期35-39,共5页
Gas Turbine Experiment and Research
