Experimental research on heat transfer characteristics of turbulence cooling of double-wall turbine blade trailing edge
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摘要:
考虑真实双层壁叶片尾缘冷却单元内部结构特征，建立冲击扰流复合冷却结构的双层壁气冷涡轮叶片尾缘模型。采用瞬态热色液晶试验方法研究了真实出流情况下扰流柱的换热特性，获得了不同几何模型（无扰流柱、半扰流柱、全扰流柱）下扰流柱冷却结构对冲击靶面换热特性的影响机理。结果表明：真实出流情况显著影响冲击靶面换热特性，使得下游冲击孔滞止区域覆盖面积更大，平均努塞尔数（
Nu ）沿出流方向下降。增加扰流柱的数量能够显著提高冲击靶面的平均努塞尔数，在C m =0.7工况下全扰流柱模型的Nu 分别比半扰流柱模型和无扰流柱模型高5.8%和21.7%。引入能够同时考量流动损失和换热能力的综合换热系数（H c）进行分析，在C m =0.7工况下全扰流柱模型相较于半扰流柱模型和无扰流柱模型分别高39%和161%。增加扰流柱能够在流动损失增加有限的情况下，显著增强叶片尾缘结构的换热能力。Abstract:Considering the internal structural characteristics of the cooling unit at the trailing edge of a real double-walled blade, the model of an impact-disturbed composite cooling structure was established. The transient Thermochromic Liquid Crystal experimental method was used to study the heat transfer characteristics of the pin-fins under the real outflow condition. Effects of the cooling structure of the pin-fins on the heat transfer at the impact target surface under different geometrical models (no pin-fin model, half-distributed pin-fins model, and full-distributed pin-fins model) were obtained. Results showed that the real outflow condition significantly affected the heat transfer characteristics of the impact target surface, which made the stagnation region of the downstream impact hole cover a larger area and the average Nusselt number (
Nu ) decrease along the outflow direction. Increasing the number of pin-fins can significantly improve the average Nusselt number of the impact target surface. Under the condition ofCm =0.7, compared with the half-distributed pin-fins model and the no pin-fin model, theNu of the full-distributed pin-fins model increased by 5.8% and 21.7%, respectively. The comprehensive heat transfer coefficient (H c), which considered both flow loss and heat transfer capacity, was introduced for analysis. Under the condition ofCm =0.7, compared with the half-distributed pin-fins model and the no pin-fin model, theH c of the full-distributed pin-fins model increased by 39% and 161%, respectively. The addition of pin-fins can significantly enhance the heat transfer capacity of the blade trailing edge structure with limited increase in flow loss.-
Key words:
- double-wall /
- turbine blade /
- trailing edge /
- pin-fin /
- real outflow
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图 1 全扰流柱模型几何及拆分后的示意图
Figure 1. Schematic diagram and split view of the model with full pin-fins
图 6 无扰流柱模型冲击靶面液晶显示图
Figure 6. Liquid crystal distribution diagram of impact target surface of model of no pin-fins
图 7 无扰流柱模型冲击靶面温度分布图
Figure 7. Temperature distribution diagram of impact target surface of model of no pin-fins
图 8 不同冲击孔中心线$ {Nu} $对比
Figure 8. Comparison of $ {Nu} $ of different impact hole centerline
图 9 各列冲击孔无量纲压力随流量比的变化规律
Figure 9. Variation of dimensionless pressure of each row of impact holes with flow ratio
图 10 $ {{C}}_{{m}}={1.0} $工况下的冲击靶面液晶显示图
Figure 10. Liquid crystal distribution diagram of impact target surface under the condition of $ {{C}}_{{m}}={1.0} $
图 11 $ {{C}}_{{m}}= 0.5 $工况下的冲击靶面液晶显示图
Figure 11. Liquid crystal distribution diagram of impact target surface under the condition of ${{C}}_{{m}}= 0.5 $
图 12 $ {{C}}_{{m}}=1.0 $工况下的冲击靶面温度分布图
Figure 12. Temperature distribution diagram of impact target surface under the condition of $ {{C}}_{{m}}=1.0 $
图 13 $ {{C}}_{{m}}=0.5 $工况下的冲击靶面温度分布图
Figure 13. Temperature distribution diagram of impact target surface under the condition of $ {{C}}_{{m}}=0.5 $
图 14 不同几何模型下冲击靶面$ Nu $随流量比的变化规律
Figure 14. Variation of $ Nu $ of impact target with flow ratio of different geometric models
图 15 不同几何模型下气膜孔出口无量纲压力随流量比的变化
Figure 15. Variation of dimensionless pressure at film hole outlet with flow ratio of different geometric models
图 16 综合换热系数随流量比变化规律
Figure 16. Variation of comprehensive heat transfer coefficient with flow ratio
表 1 模型具体尺寸
Table 1. Specific dimensions of model
符号 尺寸/mm 符号 尺寸/mm H 40 L1 105 L2 30 L3 92 L4 138 h 1.6 δ 7.2 d 13 e1 7.8 e2 3.8 P1 9 S1 9.6 P2 15.3 S2 9 P3 9.1 S3 6 W 8.9 D 18 B 141 p 1.5 q 7.3 s 4.35 
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表 2 试验工况
Table 2. Working conditions of experiment
模型 流量 无扰流柱 0.3F、0.5F、0.7F、1.0F 半扰流柱 0.3F、0.5F、0.7F、1.0F 全扰流柱 0.3F、0.5F、0.7F、1.0F
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表 3 试验仪器量程和精度
Table 3. Measuring range and accuracy of experimental instrument
仪器名称 仪器说明 精度 K型铠装热电偶 0～550 ℃ 1级（±0.25%） 涡街流量计 22.6～150 m3/h 1级 CYG1601压力传感器 0～0.4 MPa 0.3% 热色液晶（SPN100R40C20W） 40～60 ℃ ±1.0 ℃
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