几种超声速非常规压缩系统的研究

Study of several supersonic non-conventional compression surfaces

关键词:  喷气发动机  超声速进气道  压缩  激波  构型  压力分布  数值计算

Key words:  Jet engine  Supersonic inlet  Compression  Shock wave  Configuration  Pressure distribution  Numerical calculation

摘要:

根据斜激波和膨胀波理论,数值计算得到给定非常规压缩型面所形成的弯曲激波型面和壁面静压分布,同Fluent计算结果进行比较。应用Fluent软件,计算了等压力梯度设计非常规曲面压缩二元进气道、常规等熵压缩二元进气道和三楔压缩二元进气道设计点性能。研究结果表明:数值计算得到的弯曲激波型面与Fluent计算结果吻合较好。等压力梯度设计的非常规压缩型面壁面静压均匀上升,有利于防止壁面附面层分离;其压缩面长度比等熵压缩面缩短21.6%,减轻了进气道的重量。

Abstract:

The numerical method is based on the theory of oblique shock wave and expansion wave. Comparison the shape of curved shock and static pressure along curved compression surfaces between numerical method and Fluent calculation. With Fluent software, calculated the design point performance of 2-D inlets with constant pressure gradient non-convention compression surface, convention isentropic compression surface and 3-wedges compression surface, respectively. Results show: the shape of curved shock obtained by numerical method coincide better with the result of Fluent calculation ; pressure increase evenly along the compression surface designed on constant pressure gradient,that is useful to reduce the damage of boundary layer separation; compared with the isentropic compression surface, the length of curved compression surface designed on constant pressure gradient can be reduced about 21.6%.