ATR进气道改进设计及其超声速性能快速预估

Improved Design and Rapid Supersonic Performance Estimation for an ATR Engine Inlet

传统弹用ATR进气道一般为后置"X型"四旁侧二元混压式进气道。为得到构型适宜、性能优越的弹用ATR进气道,采用混压式进气道内外压缩角约束松弛的方法对ATR进气道进行改进设计,改进后进气道抗背压能力、总压比和总压恢复系数均提升50%左右。为快速分析特定来流和背压组合工况下的进气道性能,针对改进后的弹用ATR进气道建立了进气道超声速性能快速预估模型,预估模型无需识别进气道喉道和亚声速扩压段是否含有正激波。与三维数值仿真结果相比,进气道性能预估模型计算的总压恢复系数在绝大多数来流及背压组合工况下的计算误差不超过10%。ATR进气道超声速性能预估模型精度可以满足工程论证需求。

A 2D postpositional mixed-compression supersonic inlet with sweep forward high-light and X-type configuration is chosen for ATR-powered missiles.A new design method by relaxing the angle constraint of the mixed-compression inlet improves the inlet’s main performance by at least 30%.Two different estimation models are developed to assess the inlet performance in different working conditions.The preliminary model encounters a contradiction of judging the throat operating condition.The advanced model estimates the performance of throat and subsonic diffuser together.A comparison of the total pressure recoveries calculated by the advanced model to 3D CFD results shows good agreement in most working conditions considered.However,the numerical mass flow coefficients are more conservative than those obtained by the estimation method.A certain level of difference is also seen in the estimation of the maximum backpressure the inlet can resist.The estimation model is helpful to quickly predict the ATR inlet performance,to optimize the geometry,and to match with the compressor.