马赫数分布可控的二元高超弯曲压缩面优化设计 *

Optimization Design of Two-Dimensional Hypersonic Curved Compression Surface with Controllable Mach Number Distribution

关键词:  超燃冲压发动机进气道  二元高超声速进气道  弯曲激波  优化设计

Key words:  Scramjet inlet  Two-dimensional hypersonic inlet  Curved shock  Optimization design

摘要:

针对一种马赫数分布可控的二元高超弯曲压缩面进行参数化研究，获得其设计参数对压缩面性能的影响规律，在此基础上建立多项式响应面代理模型并进行多目标优化，基于优化结果设计了二元弯曲激波进气道，并与同等约束条件下的三楔进气道进行比较。结果表明:压缩面初始压缩角θ与马赫数梯度函数中的设计参数[md1]，C对压缩面性能影响最为显著；[Ma∞]=4.0时弯曲激波进气道流量系数达0.769，与三楔进气道相比，在[Ma∞]=4～7工作范围内的流量捕获能力相当，但其喉道、出口截面的总压恢复系数均高于三楔进气道，在[Ma∞]=4，6，7工况下，喉道截面总压恢复分别有6.5%，8.4%和10.7%的提高。

Abstract:

A parametric research on the curved compression surface with controllable Mach number distribution was commenced to find the effect regularity of design parameters on the performance parameters of curved compression surface. On this basis，a polynomial response surface proxy model was built to make a multi-objective optimization，and a hypersonic curved shock two-dimensional inlet was designed based on the optimization result，the performance was compared with the three-ramp compression inlet which was designed under the same constraints. Results indicate among the design parameters，the initial compress angle θ and the factor C and factor [md1] affect most. The flow coefficient of the innovative inlet is up to 0.769 at Mach 4，when Mach number ranges from 4 to 7，the two inlets have equally the same mass capture ratio，while the innovative inlet has high total pressure recovery of throat and outlet section. Compared with the relative three-ramp inlet，the total pressure recovery of throat section of the innovative inlet increased by 6.5% at Mach 4，8.4% at Mach 6，and 10.7% at Mach 7.