Influence of tapered bridge holes on impingement double wall cooling for gas turbine blade
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摘要:
为探究叶片前缘双层壁冲击冷却中连接孔结构对整体流动和换热特性的影响，建立了具有0°、5°、10°、15°、20°倾角的5个渐缩型连接孔冲击冷却模型，采用ANSYS CFX进行数值模拟。结果表明：在双层壁冲击冷却结构中将连接孔调整为渐缩形态能显著提升综合换热能力。当连接孔倾斜角从0°增大到20°，其倾角变化对结构内、外腔室流动损失影响不大；内靶面平均努塞尔数随倾角的变化几乎不变，但外靶面换热强度随着倾角增大先增强后削弱。当连接孔倾角为15°时，外靶面平均努塞尔数最大，相比标准结构提升了19.7%；总综合换热因子随连接孔倾斜角的增大呈现先增大后减小的趋势，倾角为15°时，综合换热因子达到最高，相比于标准结构提升了12.15%。
Abstract:In order to investigate the influence of the bridge holes on flow and thermal behavior of impingement double-wall cooling for gas turbine leading blades, the impingement double-wall cooling configurations with 0°, 5°, 10°, 15° and 20° tapered bridge holes were calculated by using ANSYS CFX numerical simulation. Results indicated that the tapered bridge holes can significantly enhance the comprehensive heat transfer capacity. As the angle of bridge holes increased from 0° to 20°, the angle of holes did not have a significant influence on flow loss of inner and outer chambers for the blades. Likewise, the cooling performance of the inner chamber target wall was not sensitive to the change of the bridge hole angle. With the growing angle of bridge holes, the thermal behavior of the target wall for the outer chamber increased at first and then decreased, reaching the biggest value at 15°. When the angle of bridge holes increased to 15°, its average heat transfer intensity was 19.7% higher than the case with 0° bridge holes. Similarly, the thermal performance factor of the whole configuration also became larger at first and then became smaller. The largest thermal performance factor occurred at 15° too, which was 12.15% higher than the case with 0° bridge holes.
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图 2 部分冲击冷却结构三维模型
Figure 2. Three-dimensional models of partial configurations（unit:mm）
图 3 部分结构几何尺寸 （单位：mm）
Figure 3. Geometrical dimensions of partial configurations （unit: mm）
图 7 5种结构不同截面的VXZ云图及流线图
Figure 7. VXZ contours and streamlines of five models for different planes
图 8 通过5排连接孔与外腔室交接面处的冷气速度平均值（Va,bri）随α分布示意图
Figure 8. Average velocity for cooling air with α at the interface between 5 bridge holes and outer chamber
图 9 5种结构YZ截面的VYZ云图及流线图
Figure 9. VYZ contours and streamlines of five models for YZ plane
图 10 5种结构内腔室出口流量qex,in及外腔室出口流量qex,out随α分布示意图
Figure 10. Exit mass flows for inner chamber （qex,in） and outer chamber （qex,out） of five models are distributed with α
图 11 5种结构Cpt在内、外腔室随α分布示意图
Figure 11. Cpt of five models are distributed with α for inner chamber and outer chamber
图 13 5种结构Nuac,in沿轴向分布示意图
Figure 13. Nuac,in of five models are distributed along the axial direction
图 14 5种结构Nuac,out沿轴向分布示意图
Figure 14. Nuac,out of five models are distributed along the axial direction
表 1 5种结构的各项参数对比
Table 1. Comparison of parameters for the five configurations
参数 α/（°） 0 5 10 15 20 Rein 5185 4767 4458 4393 4346 Reout 1515 1739 1875 1911 1937 Nu0,in 18.74 17.52 16.61 16.41 16.27 Nu0,out 7.00 7.82 8.30 8.43 8.52 fin 0.071 0.069 0.071 0.070 0.071 fout 0.031 0.030 0.030 0.030 0.030 ηin 5.63 6.14 6.45 6.53 6.56 ηout 2.38 2.29 2.23 2.36 2.24 ηt 4.28 4.54 4.69 4.80 4.77 
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