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为了满足组合动力进气道在宽马赫数范围内良好工作,开展了组合动力轴对称进气道设计,提出了多种轴对称进气道变几何方案以实现进气道/发动机流量匹配。理论分析及数值模拟研究了各变几何机制的可行性,对比分析各方案优劣。结果表明:外压段溢流、内压段溢流及扩压段溢流均能实现进气道/发动机流量匹配;外压段溢流变几何机制较复杂,其中改变唇罩角度和移动部分中心锥时进气道总压恢复系数较高,且移动部分中心锥时进气道压差阻力较小;内压段溢流各方案变几何机制相对简单,但溢流区域较大,斜激波易导致中心锥表面流动分离。其中采用外罩设置放气孔的形式时,进气道总压恢复系数较高,压差阻力较小;扩压段溢流方案实现简单,溢流区域小,进气道性能较好。
In order to meet the requirement of the combined power inlet to work well in the wide Mach number range, the design of the symmetrical inlet of the combined power shaft is carried out. A variety of axial symmetric inlet variable geometry schemes are proposed to achieve the inlet / engine flow matching. Theoretical analysis and numerical simulation study of the feasibility of the variable geometry mechanism, comparative analysis of the advantages and disadvantages of each program. The results show that the inlet / engine flow rate can be matched by the external pressure overflow, the internal pressure pressure overflow and the diffuser pressure overflow. The geometry mechanism of the overflow pressure in the external pressure pressure pressure gauge is more complicated, in which the lip angle and the moving part In the center cone, the total inlet pressure recovery coefficient is high, and the resistance of the inlet differential pressure is small when the center cone of the moving part is moved. The geometrical mechanism of each scheme of internal pressure section overflow is relatively simple, but the overflow area is larger, Wave-induced central cone surface flow separation. In the case of using the cover to set the vent hole, the total inlet pressure recovery coefficient is higher and the pressure drop resistance is smaller. The diffuser section overflow scheme is simple, the overflow area is small, and the inlet port performance is better.