Integrated design and experimental research for curved fore-body and 3D inward turning inlet
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摘要: 介绍了曲锥前体/内转进气道一体化的设计方法，针对进气道侧壁外扩角这一设计因素，设计了具有不同捕获形状的两套一体化构型，并完成了两套模型在马赫数Ma=6.0、0°迎角状态下的风洞试验及数值模拟对比。结果表明，基于该一体化设计方法，曲锥前缘产生的初始入射激波在设计状态下能够完全封闭进气道唇罩，进而起到抑制唇罩溢流和提高一体化构型流量捕获能力的效果。在设计条件下，进气道侧壁外扩角的增加有助于减少侧壁产生的溢流，从而提高一体化构型的流量捕获能力。同时，外扩角的增大将导致下游反压前传速度加快，从而恶化进气道的内部流场并降低一体化构型的反压特性。因此，设计此类一体化构型时，需要考虑外扩角对捕获流量和进气道出口性能的综合影响，选择合适的进气道侧壁外扩角度以达到设计需求。Abstract: An integrated design method for the curved fore-body and the 3D inward-turning inlet is proposed firstly. For the effect of the side-wall expansion angle, two models with different expansion angles are designed and constructed. Wind tunnel tests for them were carried out under the design condition Ma=6.0 and α=0°. The numerical and experimental results show that the new developed integration method is reasonable. The initial conical shock wave induced by the curved fore-body is able to match the cowl lip perfectly so that the spill flow from the cowl lip can be reduced effectively. The mass flow capture capacity of the integrated model can be improved by increasing of the expansion angle in the present work. However, the growth of the expansion angle can possibly depress the back-pressure characteristic of the integrated configuration. Therefore, a proper expansion angle should be selected to meet the overall requirement for the integrated model.
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图 1 曲锥前体/内转进气道几何布局示意图
Figure 1. Schematic of the curved fore-body and the inward turning inlet
图 7 风洞试验中试验模型安装位置示意图
Figure 7. Schematic of installation position of the test model in the wind tunnel
图 10 设计通流状态下试验模型1对称面激波形态
Figure 10. Shock wave on the symmetry plane of model 1 under design conditions
图 11 设计通流状态下试验模型2对称面激波形态
Figure 11. Shock wave in the symmetry plane of model 2 under design conditions
图 13 设计通流状态下试验模型压缩侧沿程压力分布对比
Figure 13. Pressure ratio on the ramp surfaces of two test models under design conditions
图 14 试验模型对称面马赫数云图
Figure 14. Mach number contours on the symmetry plane of two test models
图 15 两模型的横截面流场特征对比
Figure 15. Slice comparison of flow characteristics of two test models
图 16 反压条件下试验模型压缩侧沿程压力分布对比
Figure 16. Pressure ratio on the ramp surfaces of two test models under back-pressure conditions
表 1 试验模型1、2的设计参数
Table 1. Design parameters of two models
δ/(°) θ/(°) Le/m TCR ICR Ac/m2 模型1 52.48 -11.77 0.518 6.0 2.95 0.01302 模型2 52.48 52.48 0.470 6.0 2.97 0.01297 
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表 2 试验模型1、2流量捕获系数对比
Table 2. Mass flow rate ratio of two test models
Start condition Max back-pressure condition Unstart condition 试验模型1 0.819 0.821 0.366 试验模型2 0.959 0.963 0.496
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表 3 试验模型1、2抗反压能力对比
Table 3. Back-pressure performance of two test models
Start condition Max back-pressure condition Unstart condition 试验模型1 55.89 135.91 54.25 试验模型2 19.18 53.03 38.88
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表 4 试验模型1、2喉道性能对比
Table 4. Throat performance of two test models
Mathroat pthroat/p0 pthroat, t/p0, t 试验模型1 2.93 19.44 0.523 试验模型2 2.44 29.08 0.357
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