基于CFD/CSD耦合方法的旋翼降转速气动特性

张凯; 招启军; 马砾; 徐国华

doi:10.13224/j.cnki.jasp.20230074

基于CFD/CSD耦合方法的旋翼降转速气动特性

doi: 10.13224/j.cnki.jasp.20230074

南京航空航天大学航空学院直升机动力学全国重点实验室，南京 210016

基金项目: 江苏高校优势学科建设工程资助项目；国家重点实验室基金（61422202201）；国家自然科学基金（12102186）

详细信息

作者简介:
张凯（1993-），男，博士生，主要从事直升机旋翼气动及流固耦合研究

通讯作者:
招启军（1977-），男，教授、博士生导师，博士，主要从事直升机旋翼气动、结构及噪声研究。E-mail：zhaoqijun@nuaa.edu.cn

中图分类号: V211.52
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出版历程
- 收稿日期: 2023-02-14
- 网络出版日期: 2024-03-12

Slowed rotor aerodynamic characteristics using CFD/CSD coupling method

National Key Laboratory of Helicopter Aeromechanics，College of Aerospace Engineering，Nanjing University of Aeronautics and Astronautics，Nanjing 210016，China

摘要

摘要:
为研究UH-60A直升机旋翼降转速大前进比状态气动特性及反流区流动机理，采用考虑桨叶弹性变形的高精度CFD/CSD耦合方法进行数值模拟分析。CFD模块采用运动嵌套网格方法，主控方程为耦合Spalart-Allmaras（S-A）湍流模型的Navier-Stokes（N-S）方程，时间离散采用隐式lower-upper symmetric Gauss-Seidel（LU-SGS）双时间推进法；CSD模块采用中等变形梁假设，通过Newmark-Beta方法求解桨叶运动微分方程。通过UH-60A前飞状态计算值与飞行测试数据的对比验证CFD/CSD耦合方法的有效性，在此基础上，开展了UH-60A旋翼在40%工作转速不同前进比及相同前进比不同转速下气动特性研究。计算结果表明：在大前进比状态下总距对旋翼气动特性影响减弱，气动性能有所降低，大前进比产生的大反流区内存在自身桨-涡干扰、深度失速等复杂流动现象，高精度CFD/CSD耦合方法对该现象进行了有效模拟。
- 旋翼 /
- CFD/CSD耦合方法 /
- 低转速 /
- 大前进比 /
- UH-60A
Abstract:
To study the aerodynamic characteristics and the flow mechanism of reverse flow region of a slowed UH-60A rotor at high advance ratios, accurate numerical simulation analysis was carried out by the CFD/CSD coupling method considering the elastic deformation of rotor blade. The CFD module adopted a moving-embedded grid system with Navier-Stokes (N-S) equations as the governing equations, and Spalart-Allmaras（S-A） turbulence model was employed. An implicit lower-upper symmetric Gauss-Seidel (LU-SGS) dual-time algorithm was adopted for temporal discretization. As for the CSD module, the finite element method of moderate deflection beam model was employed. The blade differential equations of motion were formulated and calculated using Newmark-Beta method. The CFD/CSD coupling method validity was verified by comparing the aerodynamic loads of UH-60A with the flight test data. Then, the aerodynamic characteristics of the UH-60A rotor slowing down to 40% at different advance ratios and same advance ratio with different rotation rates were studied. The results showed that the influence of collective pitch on the aerodynamic characteristics was weakened and the aerodynamic performance was reduced at high advance ratio. Large advance ratio produced large inverse flow region, where complex flow phenomena such as blade-on-blade interactions and deep dynamic stall occurred. And the high accuracy CFD/CSD coupling method can effectively simulate these phenomena.
- rotor /
- CFD/CSD coupling method /
- slowed rotation /
- high advance ratio /
- UH-60A

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图 1 UH-60A旋翼桨叶贴体网格

Figure 1. UH-60A rotor body-fitted blade grid

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图 2 桨叶网格变形示意图

Figure 2. Schematic of blade grid deformation

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图 3 旋翼桨叶运动嵌套网格系统示意图

Figure 3. Schematic of moving-embedded grid system of rotor

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图 4 桨叶单元节点自由度示意图

Figure 4. Schematic of blade element node freedom

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图 5 旋翼CFD/CSD松耦合计算流程图

Figure 5. Flowchart of rotor CFD/CSD loose coupling method

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图 6 UH-60A旋翼桨叶平面外形

Figure 6. Planform of the UH-60A rotor

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图 7 UH-60A旋翼桨叶不同展向位置处截面法向力分布

Figure 7. UH-60A rotor sectional normal force distribution at various radial stations

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图 8 UH-60A旋翼桨叶涡量图

Figure 8. Vorticity distribution of UH-60A rotors

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图 9 UH-60A旋翼桨叶共振图

Figure 9. Resonance diagram of UH-60A rotor blade

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图 10 不同前进比拉力系数随总距变化曲线

Figure 10. Variation of thrust coefficient with collective for different advance ratios

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图 11 不同前进比功率系数随拉力系数变化曲线

Figure 11. Variation of power coefficient with thrust coefficient for different advance radios

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图 12 不同前进比阻力系数随升力系数变化曲线

Figure 12. Variation of drag coefficient with lift coefficient for different advance ratios

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图 13 不同前进比升阻比随升力系数变化曲线

Figure 13. Variation of lift to drag ratio with lift coefficient for different advance ratios

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图 14 不同展向位置处截面法向力系数对比（μ=0.4, C_T/σ=0.07）

Figure 14. Comparison of sectional normal force coefficient at different radial positions （μ=0.4, C_T/σ=0.07）

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图 15 不同展向位置处截面俯仰力矩系数对比（μ=0.4, C_T/σ=0.07）

Figure 15. Comparison of sectional pitching moment coefficient at different radial positions （μ=0.4, C_T/σ=0.07）

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图 16 不同前进比截面法向力系数对比

Figure 16. Comparison of sectional normal force coefficient for different advance ratios

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图 17 截面法向力系数及俯仰力矩系数沿展向分布曲线

Figure 17. Section normal force coefficient and pitching moment coefficient distribution along radial direction

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图 18 不同前进比下法向力系数及俯仰力矩系数分布云图

Figure 18. Contour plots of normal force coefficient and pitching moment coefficient for different advance ratios

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图 19 不同前进比下旋翼涡量分布图

Figure 19. Vorticity distribution of rotors for different advance ratios

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图 20 μ=0.8状态后行侧旋翼截面涡量图（r/R=0.55）

Figure 20. Progression of vorticity contours at μ=0.8 on the retreating side （r/R=0.55）

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图 21 不同转速截面法向力系数随方位角变化曲线（μ=0.4, C_T/σ=0.07）

Figure 21. Sectional normal force coefficient variation curve with azimuth angle at different rotating speeds （μ=0.4, C_T/σ=0.07）

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图 22 不同转速截面俯仰力矩系数随方位角变化曲线（μ=0.4, C_T/σ=0.07）

Figure 22. Sectional pitching moment coefficient variation curve with azimuth angle at different rotating speeds（μ=0.4, C_T/σ=0.07）

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图 23 不同转速截面法向力系数随方位角变化曲线（μ=0.4, C_T/σ=0.07）

Figure 23. Sectional normal force coefficient variation curve with azimuth angle at different rotating speeds（μ=0.4, C_T/σ=0.07）

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图 24 不同转速截面俯仰力矩系数随方位角变化曲线（ μ=0.4, C_T/σ=0.07）

Figure 24. Sectional pitching moment coefficient variation curve with azimuth angle at different rotating speeds（μ=0.4, C_T/σ=0.07）

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图 25 100%工作转速不同时刻旋翼涡量分布图

Figure 25. Vorticity distribution of rotors with 100% nominal revolutions per minute at different moment

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表 1 UH-60A旋翼基本参数

Table 1. Basic parameters of UH-60A rotor

旋翼参数	数值
桨叶片数 N	4
桨叶弦长c/m	0.527
旋翼半径R/m	8.175
旋翼转速Ω₀/（r/min）	258
旋翼实度σ	0.0825
挥舞铰外伸量l_e/m	0.381

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表 2 UH-60A旋翼不同转速下各阶频率结果对比

Table 2. Comparison of frequency results for UH-60A rotor blade at different rotating speeds

转速	模态	UMARC 计算值	本文计算值	误差绝对值/%
100%工作转速	1L	0.278	0.277	0.487
	1F	1.043	1.038	0.494
	2F	2.864	2.843	0.733
	1T	4.249	4.261	0.285
	2L	4.747	4.659	1.857
65%工作转速	1L	0.287	0.289	0.703
	1F	1.040	1.042	0.181
	2F	2.980	2.982	0.080
	3F	5.660	5.653	0.118
	1T	6.700	6.811	1.657
40%工作转速	1L	0.318	0.322	1.125
	1F	1.048	1.053	0.434
	2F	3.330	3.326	0.127
	3F	7.330	7.264	0.904
	2L	10.540	10.390	1.427

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