Effect of radiation on the comprehensive cooling efficiency modalization of turbine vane and its correction
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摘要:
为精确评估高温高压下涡轮叶片综合冷却效率，采用数值仿真方法研究热辐射对低工况实验结果外推精度的影响。结果显示，不计热辐射时，由低工况模化得到的高工况叶片平均综合冷却效率与真实值偏差为3.14%；计入辐射效应后，该偏差增至6.48%，表明辐射是导致模化失准的主要因素。针对该问题，选取主流雷诺数比、温度比和压力比作为关键无量纲参数，构建幂函数形式的修正模型，并通过多工况仿真数据的非线性回归确定了关联式具体形式。验证表明：应用该修正关联式后，高低工况间的最大冷却效率偏差被控制在1.21%以内，显著提升了模化预测的准确性。
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关键词:
- 涡轮叶片 /
- 综合冷却效率 /
- 导热-对流-辐射模化 /
- 数值模拟 /
- 修正关联式
Abstract:To accurately evaluate the comprehensive cooling efficiency of turbine vane under high-temperature and high-pressure conditions, numerical simulations were performed to investigate the influence of thermal radiation on the extrapolation accuracy from low operating condition experiments. The results showed that without considering thermal radiation, the deviation between the extrapolated average comprehensive cooling efficiency and the real value was 3.14%. However, when radiation effects were included, the deviation increased significantly to 6.48%, indicating that thermal radiation was a primary factor causing modeling inaccuracy. To address this issue, a correction model in the form of a power function was constructed based on key dimensionless parameters: mainstream Reynolds number ratio, temperature ratio, and pressure ratio. The specific form of the correlation was determined using non-linear regression on multi-condition simulation data. Validation results demonstrated that after applying the proposed correction correlation, the maximum deviation of cooling efficiency between high and low operating conditions was controlled within 1.21%. The proposed method can significantly improve the accuracy of modeling prediction.
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图 7 涡轮导叶不同温度下中截面马赫数云图对比（Reg=1.17×106）
Figure 7. Comparison of mid-section Mach number clouds at different temperatures for turbine guide vanes （Reg=1.17×106）
图 8 涡轮导叶高低工况毕渥数云图对比（Reg=1.17×106）
Figure 8. Comparison of high and low operating conditions of turbine guide vane Biot number clouds （Reg=1.17×106）
图 9 不同工况下叶片表面综合冷却效率展向平均
Figure 9. Spanwise-averaged surface comprehensive cooling efficiency under different operating conditions
图 10 不同工况下叶片表面平均综合冷却效率值
Figure 10. Averaged comprehensive cooling efficiency of vane surface under different operating conditions
图 11 不同工况下叶片表面平均温度
Figure 11. Averaged temperature of vane surface under different operating conditions
图 12 高低工况综合冷却效率比值图
Figure 12. Comprehensive cooling efficiency ratio diagram under high and low operating conditions
图 13 拟合点与基准工况绝对误差图
Figure 13. Absolute error of the fitted point from the reference condition
表 1 边界条件
Table 1. Boundary condition
边界条件 数值 实际发动机工况 实验室匹配工况 Reg /106 1.17 1.17 Tin/K 2 012 500，800， 1100 ，1400 ，1700 主次流压比 2 2 主次流温比 2 2 尺寸比 1 1 入口黑体辐射
温度/K2 012 500，800， 1100 ，1400 ，1700 
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表 2 叶片模化修正工况表
Table 2. Modalized correction worksheet
工况 Tin/K pg/kPa Reg/105 主流雷诺数一致 1700 2100 11.7 1400 1690 1100 1290 800 900 500 516 主流燃气压力一致 1700 2526 14.0 1400 17.5 1100 23.0 800 33.3 500 58.5 主流燃气温度一致 2 012 2100 9.73 1690 7.80 1290 5.95 900 4.00 516 2.31
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表 3 各参数比对叶片综合冷却效率比的影响
Table 3. Influence of parameters on the comprehensive cooling efficiency of vanes
恒定条件 变量 综合冷却效率比偏差/% 主流燃气压力比、雷诺数比不变 主流燃气温度比变化10% 7.73 主流燃气雷诺数比、温度比不变 主流燃气压力比变化10% 6.94 主流燃气压力比、温度比不变 主流燃气雷诺数比变化10% 6.10
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