Design and numerical simulation of a fluidic vectoring nozzle with thrust reverser
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摘要:
针对飞行器高速高机动、缩短降落距离的需求，将反推力装置与旁路式双喉道气动矢量喷管（bypass dual throat nozzle，BDTN）相结合，提出了一种反推改型气动矢量喷管（BDTN-TR）。型面优化前后的二维数值计算结果表明该喷管能在保持喷管矢量、非矢量性能优异性的同时缩短飞行器降落距离：平飞模态时，喷管推力系数和流量系数均在0.92以上；推力矢量模态时，凹腔回流区压力下降，主流上下游压差变大，喷管推力系数保持在0.93以上、流量系数保持在0.83以上，喷管落压比在2～10范围内时，推力矢量角达到了14.4°以上；反推模态时，反推效率在0.61以上，反推通道宽度对喷管反推性能的影响占主导。
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关键词:
- 旁路式双喉道气动矢量喷管（BDTN） /
- 反推力装置 /
- 推力矢量 /
- 排气系统 /
- 气动性能
Abstract:Considering the demand of high-speed, high maneuverability and shortening the landing distance of aircraft, a fluidic vectoring nozzle with thrust reverser (BDTN-TR) was proposed by combining the thrust reverser with the bypass dual throat nozzle (BDTN). The two-dimensional numerical simulation results showed that BDTN-TR can shorten the landing distance of aircraft while other performance was basically unchanged. The thrust coefficient and discharge coefficient of BDTN-TR above 0.92 could be obtained in cruise mode. In thrust vectoring mode, due to the pressure drop of separation region in the cavity, the pressure distribution of the mainstream became larger than BDTN, the thrust coefficient of BDTN-TR was above 0.93, the discharge coefficient was above 0.83, and the thrust vectoring angle reached more than 14.4° when the nozzle pressure ratio was within the range of 2 to 10. In thrust reversing mode, the thrust reverser efficiency was above 0.61, and the width of the reverse flow channel played an important role on the aerodynamic performance of the thrust reverser.
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图 5 旋转后体转轴所在区域
Figure 5. Region where rotation shafts of rotational afterbody are located
图 6 反推通道宽度为0.4H1～0.55H1时旋转后体及转轴的位置
Figure 6. Positions of rotational afterbodies and rotation shafts when width of reverse flow channel is from 0.4H1 to 0.55H1
图 8 选择的转轴（以L1 /L2=1为例）
Figure 8. Selected rotation shafts （taking L1 /L2=1 as an example）
图 9 反推通道入口倒圆半径（单位：mm）
Figure 9. Round radiuses at entrance of reverse flow channel (unit: mm)
图 13 不同网格量模型的REV-inner壁面无量纲压力分布
Figure 13. Dimensionless pressure distribution along REV-inner with different grid numbers
图 14 基准构型喷管平飞模态不同落压比的马赫数云图
Figure 14. Mach number contours of basic configuration in cruise mode under different NPRs
图 15 基准构型喷管平飞模态的性能
Figure 15. Aerodynamic performance of basic configuration in cruise mode
图 16 基准构型喷管推力矢量模态不同落压比的马赫数云图
Figure 16. Mach number contours of basic configuration in thrust vectoring mode under different NPRs
图 17 基准构型喷管推力矢量模态的性能
Figure 17. Aerodynamic performance of basic configuration in thrust vectoring mode
图 18 基准构型喷管推力矢量模态的推力矢量角
Figure 18. Thrust vectoring angles of basic configuration in thrust vectoring mode
图 19 NPR为4时不同反推通道宽度喷管的马赫数云图
Figure 19. Mach number contours with different reverse flow channels with NPR of 4
图 20 不同喷管构型反推模态的反推效率
Figure 20. Thrust reverser efficiencies of different nozzles in thrust reversing mode
图 21 不同喷管构型反推模态的反推流量系数
Figure 21. Discharge coefficients of different nozzles in thrust reversing mode
图 22 不同喷管构型反推模态的反推通道宽度
Figure 22. Reverse flow channel’s widths of different nozzles in thrust reversing mode
图 23 不同喷管构型反推模态的反推通道角度
Figure 23. Reverse flow channel’s angles of different nozzles in thrust reversing mode
图 24 NPR为4时不同转轴所对应喷管构型的马赫数云图
Figure 24. Mach number contours of different nozzles with different rotation shafts with NPR of 4
图 25 不同喷管构型反推模态的反推效率
Figure 25. Thrust reverser efficiencies of different nozzles in thrust reversing mode
图 26 不同喷管构型反推模态的反推流量系数
Figure 26. Discharge coefficients of different nozzles in thrust reversing mode
图 27 NPR为4时不同喷管构型平飞模态不同反推通道入口倒圆半径的马赫数云图
Figure 27. Mach number contours of different nozzles with different entrance of reverse flow channel’s round radiuses in cruise mode with NPR of 4
图 28 不同喷管构型平飞模态的流量系数
Figure 28. Discharge coefficients of different nozzles in cruise mode
图 29 不同喷管构型平飞模态的推力系数
Figure 29. Thrust coefficients of different nozzles in cruise mode
图 30 NPR为4时不同喷管构型推力矢量模态不同反推通道入口倒圆半径的马赫数云图
Figure 30. Mach number contours of different nozzles with different entrance of reverse flow channel’s round radiuses in thrust vectoring mode with NPR of 4
图 31 NPR为4时不同喷管构型推力矢量模态的凹腔壁面无量纲压力分布
Figure 31. Dimensionless pressure distribution along cavity wall of different nozzles in thrust vectoring mode with NPR of 4
图 32 不同喷管构型推力矢量模态的流量系数
Figure 32. Discharge coefficients of different nozzles in thrust vectoring mode
图 33 不同喷管构型推力矢量模态的推力系数
Figure 33. Thrust coefficients of different nozzles in thrust vectoring mode
图 34 不同喷管构型推力矢量模态下的推力矢量角
Figure 34. Thrust vectoring angles of different nozzles in thrust vectoring mode
图 35 NPR为4时不同喷管构型反推模态下的马赫数云图（L1/L2=1，P1）
Figure 35. Mach number contours of different nozzles in thrust reversing mode with NPR of 4 （L1/L2=1，P1）
图 36 不同喷管构型反推模态下的反推流量系数
Figure 36. Discharge coefficients of different nozzles in thrust reversing mode
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