一种外并联式TBCC变几何进气道的设计

Design of an over/under type TBCC variable geometry inlet

对一种Ma=0～7的二元外并联式TBCC变几何进气道设计开展了研究,给出了进气道总体设计思路、气动型面设计过程、变几何调节规律以及流场控制方案。初步数值仿真结果表明,该进气道满足预期的流量捕获需求,高速通道Ma=4和Ma=7时的喉道总压恢复系数分别为0.62和0.45,低速通道Ma=2.3和Ma=4时的喉道总压恢复系数分别为0.97和0.73;该变几何进气道在模态转换过程可以正常工作,没有明显的流动分离出现;由于侧板溢流,三维计算结果下的总压恢复系数与流量系数略低于二维计算结果。对三维外并联TBCC变几何进气道开展了涡轮通道扩压段设计及数值仿真研究,给出了三维模型的气动特性及涡轮通道的反压特性。

The design of a two-dimensional over/under type TBCC(Turbine based combined cycle) variable geometry inlet has been investigated including an available design method,the geometry,the variable geometry scheme and the control of the flow field of the TBCC inlet.The numerical simulation results indicated that the inlet captured air can meet the demands.The total pressure recovery of a high speed flow path throat section were 0.62 and 0.45 at Ma=4 and Ma=7,respectively.The total pressure recovery of a low speed flow path throat section were 0.97 and 0.73 at Ma=2.3 and Ma=4,respectively.The variable inlet operates well during the mode transition process,and no obvious flow separation occurs.The inlet total pressure recovery and captured three dimensional mass flow was lower than two dimensional one due to the bleed in the sidewall.The design and numerical simulation of three dimensional TBCC inlet turbine flow path diffuser has been investigated as well.The aerodynamic and back pressure characteristics of the turbine flow path have been illustrated.