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首页> 外文期刊>Journal of Engineering for Gas Turbines and Power >Impact of Swirl Flow on the Cooling Performance of an Effusion Cooled Combustor Liner
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Impact of Swirl Flow on the Cooling Performance of an Effusion Cooled Combustor Liner

机译：旋流对喷射冷却燃烧室衬板冷却性能的影响

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摘要

An experimental study on combustor liner cooling of modern direct lean injection combustion chambers using coolant ejection from both effusion cooling holes and a starter film has been conducted. The experimental setup consists of a generic scaled three sector planar rig in an open loop hot gas wind tunnel, which has been described earlier in Wurm et al. (2009, "A New Test Facility for Investigating the Interactions Between Swirl Flow and Wall Cooling Films in Combustors, Investigating the Interactions Between Swirl Flow and Wall Cooling Films in Combustors," ASME Paper No. GT2009-59961). Experiments are performed without combustion. Realistic engine conditions are achieved by applying engine-realistic Reynolds numbers, Mach numbers, and density ratios. A particle image velocimetry (PIV) measurement technique is employed, which has been adjusted to allow for high resolution near wall velocity measurements with and without coolant ejection. As the main focus of the present study is a deeper understanding of the interaction of swirl flows and near wall cooling flows, wall pressure measurements are performed for the definition of local blowing ratios and to identify the impact on the local cooling performance. For thermal investigations an infrared thermography measurement technique is employed that allows high resolution thermal studies on the effusion cooled liner surface. The effects of different heat shield geometry on the flow field and performance of the cooling films are investigated in terms of near wall velocity distributions and film cooling effectiveness. Two different heat shield configurations are investigated which differ in shape and inclination angle of the so called heat shield lip. Operating conditions for the hot gas main flow are kept constant. The pressure drop across the effusion cooled liner is varied between 1% and 3% of the total pressure. Results show the impact of the swirled main flow on the stability of the starter film and on the effusion cooling performance. Stagnation areas which could be identified by wall pressure measurements are confirmed by PIV measurements. Thermal investigations reveal reduced cooling performance in the respective stagnation areas.
机译：进行了现代直接稀薄喷射燃烧室的燃烧室衬套冷却的实验研究，该燃烧室使用了从喷射冷却孔和启动膜上喷出的冷却剂。实验装置由开环热气风洞中的通用比例三扇平面钻机组成，这在Wurm等人的文章中已有描述。 （2009年，“用于研究燃烧室中旋流与壁冷却膜之间的相互作用，研究燃烧室中旋流与壁冷却膜之间的相互作用的新测试设施”，ASME文件GT2009-59961）。实验无需燃烧即可进行。通过应用发动机逼真的雷诺数，马赫数和密度比来实现逼真的发动机条件。采用了粒子图像测速（PIV）测量技术，该技术已经过调整，可以在有和没有冷却剂喷射的情况下进行高分辨率的近壁速度测量。由于本研究的主要重点是对旋流与近壁冷却流之间相互作用的更深入了解，因此执行壁压测量以定义局部鼓风比并确定对局部冷却性能的影响。为了进行热学研究，采用了红外热像仪测量技术，该技术可以对喷射冷却的衬管表面进行高分辨率的热学研究。根据近壁速度分布和薄膜冷却效率，研究了不同的隔热屏几何形状对流场和冷却薄膜性能的影响。研究了两种不同的隔热板配置，它们的形状和倾斜角度与所谓的隔热板唇不同。热气主流的运行条件保持恒定。流出冷却的衬管上的压降在总压力的1％和3％之间变化。结果表明，旋流主流对起动器薄膜的稳定性和喷射冷却性能的影响。可以通过壁压力测量确定的停滞区域通过PIV测量确定。热学调查表明，各个停滞区域的冷却性能下降。

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  • 来源
    《Journal of Engineering for Gas Turbines and Power》 |2012年第12期|121503.1-121503.9|共9页
  • 作者

    B. Wurm; A. Schulz; H.-J. Bauer; M. Gerendas;

  • 作者单位

    Institut fuer Thermische Stroemungsmaschinen, Karlsruher Institut fuer Technologie (KIT), Kaiserstrae 12, 76131 Karlsruhe, Germany;

    Institut fuer Thermische Stroemungsmaschinen, Karlsruher Institut fuer Technologie (KIT), Kaiserstrae 12, 76131 Karlsruhe, Germany;

    Institut fuer Thermische Stroemungsmaschinen, Karlsruher Institut fuer Technologie (KIT), Kaiserstrae 12, 76131 Karlsruhe, Germany;

    Combustor Aerothermal and Cooling, Rolls-Royce Deutschland Ltd & Co KG, Eschenweg 11, Dahlewitz 15827 Blankenfelde-Mahlow, Germany;

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