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首页> 外文期刊>Journal of turbomachinery >Film-Cooling Performance of a Turbine Vane Suction Side: The Showerhead Effect on Film-Cooling Hole Placement for Cylindrical and Fan-Shaped Holes
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Film-Cooling Performance of a Turbine Vane Suction Side: The Showerhead Effect on Film-Cooling Hole Placement for Cylindrical and Fan-Shaped Holes

机译：涡轮叶片吸入侧的薄膜冷却性能：莲蓬头对圆柱孔和扇形孔薄膜冷却孔位置的影响

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摘要

In this paper, the transient IR-thermography method is used to investigate the effect of showerhead cooling on the film-cooling performance of the suction side of a turbine guide vane working under engine-representative conditions. The resulting adiabatic film effectiveness, heat transfer coefficient (HTC) augmentation, and net heat flux reduction (NHFR) due to insertion of rows of cooling holes at two different locations in the presence and absence of the showerhead cooling are presented. One row of cooling holes is located in the relatively high convex surface curvature region, while the other is situated closer to the maximum throat velocity. In the latter case, a double staggered row of fan-shaped cooling holes has been considered for cross-comparison with the single row at the same position. Both cylindrical and fan-shaped holes have been examined, where the characteristics of fan-shaped holes are based on design constraints for medium size gas turbines. The blowing rates tested are 0.6, 0.9, and 1.2 for single and double cooling rows, whereas the showerhead blowing is maintained at constant nominal blowing rate. The adiabatic film effectiveness results indicate that most noticable effects from the showerhead can be seen for the cooling row located on the higher convex surface curvature. This observation holds for both cylindrical and fan-shaped holes. These findings suggest that while the showerhead blowing does not have much impact on this cooling row from HTC enhancement perspective, it is influential in determination of the HTC augmentation for the cooling row close to the maximum throat velocity. The double-row fan-shaped cooling seems to be less affected by an upstream showerhead blowing when considering HTC enhancement, but it makes a major contribution in defining adiabatic film effectiveness. The NHFR results highlight the fact that cylindrical holes are not significantly affected by the showerhead cooling regardless of their position, but showerhead blowing can play an important role in determining the overall film-cooling performance of fan-shaped holes (for both the cooling row located on the higher convex surface curvature and the cooling row close to the maximum throat velocity), for both the single and the double row cases.
机译：本文采用瞬态红外热成像方法研究了莲蓬头冷却对在发动机代表性工况下工作的涡轮导向叶片吸入侧薄膜冷却性能的影响。呈现了由于存在和不存在喷头冷却而在两个不同位置插入冷却孔行而导致的绝热膜效率，传热系数（HTC）增大和净热通量减少（NHFR）。一排冷却孔位于相对较高的凸面曲率区域，而另一排则更靠近最大喉道速度。在后一种情况下，考虑将双排交错的扇形冷却孔与同一位置的单排进行交叉比较。已经检查了圆柱孔和扇形孔，其中扇形孔的特性基于中型燃气轮机的设计约束。对于单排和双排冷却排，测试的吹风速率分别为0.6、0.9和1.2，而喷头的吹风速率则保持恒定。绝热膜的有效性结果表明，对于位于较高凸表面曲率的冷却排，可以看到喷头的最明显影响。这种观察对于圆柱孔和扇形孔均成立。这些发现表明，从HTC增强的角度看，莲蓬头吹气对冷却排的影响不大，但它对确定接近最大喉咙速度的冷却排的HTC的增加有影响。考虑提高HTC时，双排扇形冷却似乎不受上游喷头吹动的影响，但在定义绝热膜的有效性方面做出了重大贡献。 NHFR结果凸显了以下事实：无论喷淋头的位置如何，圆柱孔都不会受到喷头冷却的显着影响，但是喷头的吹气在确定扇形孔的整体薄膜冷却性能方面起着重要作用（对于两个冷却排都位于对于单排和双排情况，在较高的凸表面曲率和冷却排接近最大喉道速度时）。

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  • 来源
    《Journal of turbomachinery》 |2015年第9期|091005.1-091005.11|共11页
  • 作者

    Hossein Nadali Najafabadi; Matts Karlsson; Mats Kinell; Esa Utriainen;

  • 作者单位

    Department of Management and Engineering, Linkoeping University, Linkoeping 581 83, Sweden;

    Department of Management and Engineering, Linkoeping University, Linkoeping 581 83, Sweden;

    Siemens Industrial Turbomachinery AB, Finspang 612 83, Sweden;

    Siemens Industrial Turbomachinery AB, Finspang 612 83, Sweden;

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