向心涡轮跨声速导向叶片叶型设计及验证

欧阳玉清; 李维; 曾飞; 潘尚能; 李恩华; 刘存良

doi:10.13224/j.cnki.jasp.20220820

向心涡轮跨声速导向叶片叶型设计及验证

doi: 10.13224/j.cnki.jasp.20220820

1.
西北工业大学动力与能源学院，西安 710129
2.
中国航发湖南动力机械研究所，湖南株洲 412002

详细信息

作者简介:
欧阳玉清（1986-），男，高级工程师，博士生，主要从事航空发动机涡轮气动设计

中图分类号: V231.1
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- 文章访问数: 121
- HTML浏览量: 35
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- 被引次数: 0
出版历程
- 收稿日期: 2022-10-26
- 网络出版日期: 2023-03-16

Design and validation of transonic nozzle guide vane profile of radial-inflow turbine

1.
School of Power and Energy，Northwestern Polytechnical University，Xi’an 710129，China
2.
Hunan Aviation Powerplant Research Institute， Aero Engine Corporation of China，Zhuzhou Hunan 412002，China

摘要

摘要:
以某先进辅助动力装置用膨胀比5.0级向心涡轮跨声速导叶为研究对象，从消除几何喉部前局部超声区及削弱尾缘激波强度两方面着手，对导向叶片进行了优化改进及叶栅试验验证，结果表明：采用大正攻角、小安装角的设计思路，减小喉部前吸力面叶型曲率，降低进口段的通道面积，提高了叶型前段负荷，消除了喉部前的过膨胀区，喉部前气流加速更为均匀；在吸力面喉部后构建局部内凹结构，可将原方案中吸力面尾缘处一道较强的激波变为两道较弱的激波，峰值马赫数降低，尾缘逆压梯度减小，尾缘激波强度得以削弱。试验结果显示：在出口马赫数0.9～1.1范围内，优化后叶型能量损失系数均有所降低，在出口马赫数为1.1时，能量损失系数可降低近20%。
- 向心涡轮 /
- 跨声速叶栅 /
- 导向器叶片 /
- 叶型设计 /
- 激波损失
Abstract:
Taking the transonic nozzle guide vane of a radial-inflow turbine with expansion ratio of 5.0 for an advanced auxiliary power unit as the research object, the vane profile was optimized and cascade tests were conducted by eliminating the local ultrasonic region in front of the throat and weakening the shock wave intensity at the trailing edge. The research showed that by adopting the design idea of large positive incidence angle and small installation angle, and reducing the curvature of suction side before the throat, reducing the flow area of inlet duct, the load in front of the blade profile was improved, the over expansion area before the throat was eliminated, and the airflow acceleration was more uniform. A local concave structure was constructed behind the throat of the suction surface, which can transform one strong shock wave at the trailing edge of the suction surface into two relatively weak shock waves. The peak Mach number decreased, and the adverse pressure gradient at the trailing edge decreased, weakening the strength of the trailing edge shock wave. The test results indicated that the energy loss coefficient of optimized profile dropped as the cascade exit Mach numbers varied from 0.9 to 1.1, and the energy loss coefficient dropped nearly 20% when the exit Mach number was 1.1.
- radial-inflow turbine /
- transonic cascade /
- nozzle guide vane /
- profile design /
- shock loss

HTML

图 1 基准叶型示意图

Figure 1. Schematic diagram of reference blade profile

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图 2 吸力面叶型曲率

Figure 2. Profile curvature of suction side

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图 3 典型向心涡轮导叶叶型表面静压分布

Figure 3. Static pressure distribution of typical radial-inflowturbine nozzle guide vane

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图 4 叶型对比示意图

Figure 4. Different vane profiles

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图 5 叶栅相对通道宽度对比

Figure 5. Comparison of relative cascade channel width

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图 6 导叶计算网格

Figure 6. Vane blade computing grid

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图 7 涡轮叶栅转换示意图

Figure 7. Illustration of cascade transformation

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图 8 叶型表面马赫数分布对比

Figure 8. Comparison of Mach number distributions on blade surface

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图 9 叶型中截面马赫数分布

Figure 9. Comparison of Mach number contours on mid-span

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图 10 叶中截面出口周向损失对比

Figure 10. Loss distribution along circumferential direction at the exit of mid-span

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图 11 导叶中截面静熵分布

Figure 11. Comparison of static entropy distribution on mid-span

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图 12 马赫数计算值与试验值对比

Figure 12. Comparison of calculated and tested Mach number distributions

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图 13 计算与试验出口周向能量损失系数对比

Figure 13. Comparison of calculated and tested exit circumferential energy loss coefficient distributions

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图 14 不同叶型周向出口马赫数试验结果对比

Figure 14. Comparison of tested exit circumferential Mach number with different profiles

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图 15 能量损失系数随出口马赫数变化对比

Figure 15. Comparison of energy loss coefficient with different exit Mach number

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表 1 叶型几何参数

Table 1. Geometric parameters of profile

几何参数	Vane A	Vane B
导叶叶片数 N_v	23	23
径向弦长 b_r/mm	19.0	19.0
尾缘半径 r_t/mm	0.4	0.4
进口构造角 α₁/（°）	90	135
出口构造角 α₂/（°）	19	19
尾缘楔角 ω₂/（°）	5.0	4.0
喉部收敛角α_c/（°）	20.0	15.0
安装角 γ/（°）	33.0	29.0
喉宽o/mm	8.78	8.78
栅距s/mm	28.53	28.53

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表 2 叶型损失系数对比

Table 2. Comparison of blade profile loss coefficient

损失系数	Vane A	Vane B
附面层摩擦损失+ 尾缘前激波损失系数	0.01974	0.01655
尾迹损失+尾缘后激波损失系数	0.01553	0.01400
叶型总损失系数	0.05201	0.04861

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