两级跨声风扇气动性能的实验和数值模拟

杨加寿; 魏新谛; 唐雨萌; 冀国锋; 柳阳威

doi:10.13224/j.cnki.jasp.20240306

两级跨声风扇气动性能的实验和数值模拟

doi: 10.13224/j.cnki.jasp.20240306

杨加寿^{1, 4,},
魏新谛^{2, 3},
唐雨萌^{2, 3},
冀国锋¹,
柳阳威^{2, 3,*, ,}

1.
中国航发贵阳发动机设计研究所，贵阳 550081
2.
北京航空航天大学能源与动力工程学院，北京 100191
3.
北京航空航天大学航空发动机气动热力国家级重点实验室，北京 100191
4.
西北工业大学国家卓越工程师学院，西安 710072

基金项目: 国家自然科学基金（52106039）；中国航发集团产学研合作项目（HFZL2022CXY001，HFZL2023CXY002）；北京航空航天大学博士研究生卓越学术基金

详细信息

作者简介:
杨加寿（1989-），男，高级工程师，博士生，从事航空发动机压气机气动设计研究。E-mail：yangjs99@yeah.net

通讯作者:
柳阳威（1980-），男，教授、博士生导师，博士，主要从事叶轮机内复杂流动预测及控制方法研究。E-mail：liuyangwei@126.com

中图分类号: V231.3
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出版历程
- 收稿日期: 2024-05-14
- 网络出版日期: 2024-09-20

Experimental and numerical study on aerodynamic performance of transonic two-stage fan

YANG Jiashou^{1, 4
,},
WEI Xindi^{2, 3},
TANG Yumeng^{2, 3},
JI Guofeng¹,
LIU Yangwei^{2, 3,*
, ,}

1.
Guiyang Engine Design Research Institute，Aero Engine Corporation of China，Guiyang 550081，China
2.
School of Energy and Power Engineering，Beihang University，Beijing 100191，China
3.
National Key Laboratory of Science and Technology on Aero-Engine Aero-thermodynamics，Beihang University，Beijing 100191，China
4.
National Elite Institute of Engineering，Northwestern Polytechnical University，Xi’an 710072，China

摘要

摘要:
对某两级跨声风扇开展了实验和数值模拟研究，该跨声风扇的两级转子均采用前掠设计，第一级静子采用常规构型，末级静子则采用串列构型。对不同转速下的特性参数进行了实验测量，采用Spalart-Allmaras（SA）湍流模型和基于螺旋度修正的SA-Helicity湍流模型，对风扇100%转速和80%转速的特性进行了定常数值模拟。结果表明：SA模型过低预测了风扇的稳定裕度，SA-Helicity模型对稳定裕度、效率和压比特性的预测精度较SA模型明显提升。风扇第二级的平均负荷高于第一级，工况向近失速点移动时，总温和总压增加的贡献也主要来自于第二级。风扇主要损失来源自转子激波引起的边界层增厚和静子端区的角区分离。特别是在近失速点，第一级静子和第二级串列静子的第一排叶片端区产生的角区分离结构是引起损失剧烈增加的主要原因。
- 跨声风扇 /
- 多级风扇/压气机 /
- 湍流模型 /
- 高负荷 /
- 气动性能
Abstract:
Experimental research and numerical simulation were conducted on a two-stage transonic fan. Both two rotors of the two-stage fan adopted the forward-swept design, and the last stage stator employed a tandem configuration. Experimental measurements of characteristic parameters were conducted at different rotation speeds. Then, steady numerical simulations of the fan were conducted at 100% rotation speed and 80% rotation speed using the Spalart-Allmaras (SA) turbulence model and the SA-Helicity turbulence model. Results indicated that the SA model underpredicted the stall margin, while the SA-Helicity model significantly improved the prediction accuracy of the stall margin, the efficiency, and the pressure ratio. The loading subjected by the second stage was higher than that by the first stage. The second stage primarily contributed to the increase of total temperature and pressure as the operating condition moved towards the near-stall point. The shock wave and the corner separation constituted the primary sources of loss. In the near-stall condition, a large corner separation at the first stator and the first row of the stage tandem stator was the main reason for the increase of losses.
- transonic fan /
- multi-stage fan/compressor /
- turbulence model /
- high loading /
- aerodynamic performance

HTML

图 1 两级风扇流道和三维几何示意图

Figure 1. Meridional plane and three-dimensional geometry of the two-stage fan

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图 2 两级风扇实验设备机械部分

Figure 2. Mechanical components of the two-stage fan experimental rig

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图 3 风扇性能实验测量截面与测点布局示意图

Figure 3. Schematic diagram of the experiment rig and the distribution of measurement points

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图 4 两级风扇计算域和计算网格

Figure 4. Computational domain and mesh for the two-stage fan

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图 5 80%和100%转速的特性曲线

Figure 5. Performance characteristics at 80% and 100% speed

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图 6 各叶片排出口周向平均参数的展向分布对比

Figure 6. Comparison of the circumferentially averaged parameters in the spanwise direction

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图 7 最高效率点和近失速点气动参数展向分布

Figure 7. Spanwise distribution of aerodynamic parameters at the peak efficiency condition and the near stall condition

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图 8 最高效率点和近失速点不同叶高静压比

Figure 8. Static pressure ratio at the peak efficiency condition and near stall point condition

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图 9 10%、50%和95%叶高的马赫数分布云图

Figure 9. Mach number contour at the 10%, 50%, and 95% span plane

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图 10 100%转速SA-Helicity模型预测的壁面极限流线和壁面摩擦因数云图

Figure 10. Wall Streamlines and friction coefficient predicted by the SA-Helicity model at the 100% speed

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图 11 末级串列静子的流动拓扑和出口截面熵产率分布（等值面为L_z=±2 000 s⁻¹）

Figure 11. Flow topology and distribution of the entropy production rate at the exit plane of the last stage tandem stator （Isosurface of L_z=±2 000 s⁻¹）

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