Flow losses characteristics of BLI inlet
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摘要:
用数值仿真手段，对进气道内流总压损失采用逐段对比分析的方法，研究了附面层吸入式（BLI）进气道相对于常规S弯进气道的内流总压损失特性。结果表明：进气道出口马赫数不变，较低来流马赫数和较高来流马赫数工况下（方案对应马赫数0.3以下和马赫数0.6以上），BLI进气道产生的流动损失比常规S弯进气道的大，差量达2.4%；中等来流马赫数工况下（本文方案对应马赫数0.3与马赫数0.6之间），BLI进气道产生的流动损失比常规S弯进气道的略小，差量在0.3%以内；流动损失特性间的差异是由于BLI进气道进口前壁面与进口低能附面流改变了进口段流动特性、及在S弯管道内发展的综合作用结果。
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关键词:
- 附面层吸入式（BLI）进气道 /
- S弯进气道 /
- 飞/发一体化 /
- 附面层 /
- 流动损失
Abstract:In order to study the difference and mechanism of the internal flow total pressure loss between the boundary layer ingestion (BLI) inlet and the conventional S-shaped inlet, numerical simulation method was applied and step-by-step comparative analysis of the total pressure loss was carried out. The results showed that, when fan-face Mach number was kept unchanged, the flow loss of BLI inlet was larger than that of the conventional S-shaped inlet under the working conditions of relatively lower and higher Mach number of free-stream (corresponding to below 0.3 or above 0.6), and the maximum difference was 2.4 percent. Under the working condition of medium Mach number of free-stream (corresponding to between 0.3 and 0.6), the flow loss generated by the BLI inlet was slightly smaller than that of the conventional S-shaped inlet, and the maximum difference was 0.3 percent. The combined effect of the fore-wall of the BLI inlet and the low-energy boundary flow changed the flow characteristics in the inlet and developed rapidly in the diffuser of the S-shaped pipeline, leading to the difference in flow loss characteristics.
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图 8 进气道对称剖面上的总压恢复系数云图
Figure 8. Contour of total pressure recover coefficient in symmetry plane of inlet
图 10 不同来流马赫数入口前截面相对总压降曲线
Figure 10. Relative total pressure drop at inlet front plane with different incoming Mach number
图 11 BLI进气道入口前截面总压恢复系数云图
Figure 11. Contour of total pressure recover coefficient at the highlight plane of BLI S-shaped inlet
图 12 不同来流马赫数进气道内相对总压降曲线图
Figure 12. Relative total pressure drop in inlet with different incoming Mach number
图 16
$M{a_\infty } = 0.1$ 时BLI进气道与S弯进气道唇口流线分布Figure 16. Streamline around the lip of BLI and S-shaped inlet at
$M{a_\infty } = 0.1$ 
图 17
$M{a_\infty } = 0.4$ 时BLI进气道与S弯进气道唇口流线分布Figure 17. Streamline around the lip of BLI and S-shaped inlet at
$M{a_\infty } = 0.4$ 
图 18
$M{a_\infty } = 0.8$ 时BLI进气道与S弯进气道唇口流线分布Figure 18. Streamline around the lip of BLI and S-shaped inlet at
$M{a_\infty } = 0.8$ 
图 19 进气道进口截面和喉道截面上总压恢复云图（
$M{a_\infty } = 0.4$ ）Figure 19. Contour of total pressure recover coefficient at entrance section and throat section of inlet （
$M{a_\infty } = 0.4$ ）
图 21 进气道壁面流线及扩压段进出口总压分布云图
Figure 21. Wall streamline of inlet and contour of total pressure at entrance and exit section of diffuser
表 1 网格无关性计算结果（
$M{a_\infty } = 0.4$ ）Table 1. Results of mesh independent calculation （
$M{{{a}}_\infty } = 0.4$ ）网格数量/104 进气道出口总压恢复系数 436 0.9796 672 0.9733 825 0.9715 1078 0.9712 
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