Improved design of hovering efficiency of ducted propeller with large blade tip clearance based on grooved duct configuration
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摘要:
为提高涵道螺旋桨气动效率，需要很小桨涵间隙，导致加工和使用维护成本大幅增加。为此基于沟槽涵道构型，研究大桨涵间隙时改进效率的方法。基于雷诺平均NS方程和MRF方法展开计算研究。首先基于常规无沟槽涵道构型开展分析，当间隙比从1倍基准间隙比增大到4倍时，悬停效率下降超25%，桨涵间隙增加导致效率显著下降。其次基于沟槽涵道构型开展分析，发现桨尖位置和沟槽外形是决定悬停效率的关键变量。通过向沟槽内适当延伸桨尖，可以在间隙比为6.7倍基准间隙比时，悬停效率无明显下降，若采用圆形沟槽，则间隙比为2倍基准间隙比时，悬停效率反而提高5.2%，最终通过测力试验验证，证明沟槽涵道构型可在大桨涵间隙时改进气动效率，降低加工和使用维护成本。
Abstract:In order to improve the aerodynamic efficiency of the ducted propeller, high machining and assembly accuracy were required to maintain a small clearance between the blade tip and the duct, resulting in a significant increase in the processing, operation and maintenance costs. To solve this problem, the design philosophy of improving hovering efficiency with large blade clearance was studied based on the grooved duct configuration. Calculation was carried out based on Reynolds averaged NS equation and multiple reference frame model. Firstly, based on the baseline design of a conventional ducted propeller, it was found that when the blade tip clearance ratio increased to four times the reference tip clearance ratio, the hovering efficiency decreased by more than 25%. Therefore, the increase of the blade tip clearance led to a significant decrease in the hovering efficiency. Secondly, based on parametric analysis, it was found that tip position and groove shape are key variables determining the hovering efficiency. By properly extending the blade tip into the groove, the hovering efficiency can be equivalent to that of the baseline design when the blade tip clearance ratio reached 6.7 times of the reference tip clearance ratio. If the circular groove was used, the hovering efficiency can be increased by 5.2% when the blade tip clearance ratio was 2 times of the reference tip clearance ratio. The results of numerical simulation and experiments indicated that the grooved duct configuration can improve the aerodynamic efficiency and reduce costs with a large tip clearance ratio.
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图 6 不同间隙比涵道螺旋桨的$ C_{T} $
Figure 6. $ C_{T} $ of ducted propeller with different tip clearance ratio
图 7 不同间隙比模型的${\eta _0}$对比
Figure 7. Comparison of ${\eta _0}$ with different tip clearance ratio
图 12 M1～M4的$ C_{T} $、$ C_p $和${\eta _0}$对比
Figure 12. Comparison of $ C_{T} $、$ C_p $ and ${\eta _0}$ for M1—M4
图 13 不同沟槽涵道螺旋桨展向升力分布图
Figure 13. Spanwise lift distribution of different grooved duct propeller
图 16 M2、M5、M6的$ C_{T} $、$ C_p $和${\eta _0}$对比
Figure 16. Comparison of $ C_{T} $，$ C_p $ and ${\eta _0}$ for M2，M5，M6
图 17 M2、M6涵道内壁面压力系数对比图
Figure 17. Comparison of pressure coefficient on duct inner surface for M2，M6
图 18 M2、M5、M6螺旋桨升力分布对比图
Figure 18. Spanwise lift distribution for propeller of M2, M5 and M6
图 19 M2、M7、M8的$ C_{T} $、$ C_{p} $和${\eta _0}$对比
Figure 19. Comparison of $ C_{T} $，$ C_{p} $ and ${\eta _0}$ for M2，M7，M8
图 20 M2、M7、M8螺旋桨升力分布对比图
Figure 20. Spanwise lift distribution for propeller of M2, M7 and M8
图 21 M2、M9、M10的$ C_{T} $、$ C_{p} $和${\eta _0}$对比
Figure 21. Comparison of $ C_{T} $，$ C_{p} $ and ${\eta _0}$ for M2，M9，M10
表 1 网格无关性验证计算结果（
4000 r/min）Table 1. Mesh independent test results （
4000 r/min）网格
数量/104推力
系数转矩
系数推力
误差/%转矩
误差/%730 0.1984 0.0135 5.16 7.14 1224 0.2040 0.0133 2.50 5.55 1652 0.2057 0.0132 1.67 4.76 试验数据 0.2092 0.0126 
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表 2 无沟槽涵道对比算例设定
Table 2. Settings for non-grooved ducted propellers
参数 数值与说明 高度/km 0 螺旋桨转速/（r/min） 4000 攻角/（°） 0 间隙比 0, $ {\varDelta _{\text{b}}} $, $ 2{\varDelta _{\text{b}}} $, $ 3{\varDelta _{\text{b}}} $, $ 4{\varDelta _{\text{b}}} $，孤立螺旋桨
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表 3 不同沟槽形状涵道螺旋桨计算模型
Table 3. Grooved ducted propeller test cases with different groove shape
模型编号 形状 沟槽尺寸/mm 间隙比 深度 高度 M1 方形 10 10 ${\varDelta _{\text{b}}}$ M2 方形 10 10 $4{\varDelta _{\text{b}}}$ M3 方形 10 10 $6.7{\varDelta _{\text{b}}}$ M4 方形 10 10 $7.7{\varDelta _{\text{b}}}$ M5 方形 10 14 $4{\varDelta _{\text{b}}}$ M6 方形 10 18 $4{\varDelta _{\text{b}}}$ M7 方形 13.2 10 $5.5{\varDelta _{\text{b}}}$ M8 方形 6.26 10 ${\varDelta _{\text{b}}}$ M9 圆形 10 10 $4{\varDelta _{\text{b}}}$ M10 圆形 5 10 $2{\varDelta _{\text{b}}}$
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