TBCC用轴对称进气道流量控制技术研究

推进技术 ›› 2013, Vol. 34 ›› Issue (12): 1606-1615.

• 气动热力学与总体技术 • 上一篇下一篇

TBCC用轴对称进气道流量控制技术研究

王亚岗,袁化成,郭荣伟

江苏省航空动力系统重点实验室南京航空航天大学能源与动力学院,江苏南京 210016;江苏省航空动力系统重点实验室南京航空航天大学能源与动力学院,江苏南京 210016;江苏省航空动力系统重点实验室南京航空航天大学能源与动力学院,江苏南京 210016

发布日期:2021-08-15
作者简介:王亚岗(1988—),硕士生,研究领域为内流气体动力学。E-mail:wygqq@126.com

Research on Mass-Flow Controlling Technology of TBCC Axisymmetric Inlet

Jiangsu Province Key Laboratory of Aerospace Power Systems,College of Energy and Power, Nanjing University of Aeronautics and Astronautics , Nanjing 210016,China;Jiangsu Province Key Laboratory of Aerospace Power Systems,College of Energy and Power, Nanjing University of Aeronautics and Astronautics , Nanjing 210016,China;Jiangsu Province Key Laboratory of Aerospace Power Systems,College of Energy and Power, Nanjing University of Aeronautics and Astronautics , Nanjing 210016,China

Published:2021-08-15

摘要/Abstract

摘要： 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。 

关键词: 组合动力;轴对称进气道;变几何;流量匹配;数值模拟 

Abstract: To meet requirement of good performance for TBCC inlet in a wide range of Mach number, the TBCC axisymmetric inlet was designed. Variety of variable geometrical plans of axisymmetric inlet was put forward to realize inlet/engine mass-flow matching. Theoretical analysis and numerical simulation was carried out to study the feasibility of the mechanism of variable geometry and analyse the advantages and disadvantages of the schemes. The results show that external compression bleeding can achieve mass-flow matching as well as internal compression bleeding and diffuser bleeding. The mechanism of variable geometry of external compression bleeding plans was more complex than that of internal compression bleeding and diffuser bleeding. The total pressure recovery coefficient was higher while changing the angle of cowl and moving part of spike and the pressure drag was smaller when moving part of spike. If bleeding area is large, it can result in spike surface flow separation by oblique shock wave. While taking the form of setting vent holes, the inlet total pressure recovery coefficient is higher and the pressure drag is smaller. The variable geometry of diffuser bleeding is feasible,its bleeding area is small and the inlet performance is improved. 

Key words: Combined engine; Axisymmetric inlet; Variable geometry; Mass-flow matching; Numerical simulation

王亚岗,袁化成,郭荣伟. TBCC用轴对称进气道流量控制技术研究[J]. 推进技术, 2013, 34(12): 1606-1615.

WANG Ya-gang, YUAN Hua-cheng, GUO Rong-wei. Research on Mass-Flow Controlling Technology of TBCC Axisymmetric Inlet[J]. Journal of Propulsion Technology, 2013, 34(12): 1606-1615.

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TBCC用轴对称进气道流量控制技术研究

Research on Mass-Flow Controlling Technology of TBCC Axisymmetric Inlet

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