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为了实现涡轮基组合循环(TBCC)推进系统平稳模态转换过程的模拟,在前期风洞试验研究的基础上对串联式TBCC进气道模态转换模拟器进行重新设计。采用线性化及非对称的思路对该模拟器进行设计并对其特性展开数值仿真研究。结果表明:该模拟器不仅需要模拟发动机工况改变引起的背压变化,而且能通过流通截面面积线性变化,实现两个通道的流量分配。该装置的特点是能保证模态转换过程中每一点的涡轮/冲压通道的总堵塞比不变,使本文所研究的进气道在总堵塞比保持为65%时进行模态转换,结尾激波基本维持在喉道等直段内且进气道出口马赫数基本维持在0.30,流量系数基本为0.45,涡轮/冲压通道流量呈线性变化,与预期目标一致。
In order to simulate the steady state mode transition process of TBCC propulsion system, the tandem TBCC intake mode switch simulator was redesigned on the basis of the previous wind tunnel tests. The simulator is designed using linear and asymmetric method and its numerical simulation is carried out. The results show that the simulator not only needs to simulate the change of back pressure caused by the change of engine operating conditions, but also can realize the flow distribution of two channels through the linear change of flow cross-sectional area. The characteristic of this device is to ensure that the total blockage ratio of the turbine / ramification channel at each point during the modal conversion is unchanged, so that the inlet channel studied in this article modal transitions when the total blockage ratio is maintained at 65% Wave basically maintained in the throat and other straight sections and the Mach Mach number at the inlet was basically maintained at 0.30, the flow coefficient is basically 0.45, Turbine / punch channel flow showed a linear change, in line with the expected target.