Targeting higher efficiencies and lower fuel consumption of turbomachines, heat transfer and profile loss are research topics of particular interest. In contrast to that, the interaction of both was, so far, rarely investigated, but gains in importance in recent research activities. The profile loss of engine components can be characterised by the airfoil wakes at the blade rows utilising established measurement and evaluation methods for which an adiabatic flow is typically supposed. To enable the investigation of the influence of heat transfer at the blade on the loss characteristics, a novel evaluation procedure was set up. In addition to the pneumatic data, the total temperature in the airfoil wake at a linear cascade was measured by means of a five-hole probe with an integrated thermocouple. For the evaluation and analysis of these data, different definitions of the loss coefficient were investigated and, finally, extended to account for thermal aspects. Furthermore, established techniques to average the local wake data were applied and compared with special focus to their suitability for non-adiabatic cases. Moreover, an extended version of the mixed-out average as defined by Amecke was utilised applying not only a far-reaching consideration of a temperature gradient but also the inclusion of the third spatial dimension to enable the evaluation of field traverses in addition to single wake traverses. These techniques were applied to wake measurement data from a linear compressor cascade gained in a special test set-up in the high-speed cascade wind tunnel for different operating points and different blade temperatures. The suitability of the new methods could be proven, and initial steps of the aerodynamic analysis of the resulting data are presented. Thereby, the acquired techniques turned out as powerful methods for the evaluation of wake traverses on compressor and turbine cascades under non-adiabatic conditions.

中文翻译：

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考虑热效应的线性级联损耗确定

针对涡轮机的更高效率和更低燃料消耗、传热和轮廓损失是特别感兴趣的研究课题。与此相反，迄今为止，两者的相互作用很少被研究，但在最近的研究活动中变得越来越重要。发动机部件的轮廓损失可以通过使用已建立的测量和评估方法在叶排处的翼型尾流来表征，绝热流通常被假定为该方法。为了能够研究叶片传热对损耗特性的影响，建立了一种新的评估程序。除了气动数据外，线性级联的翼型尾流中的总温度是通过带有集成热电偶的五孔探头测量的。为了评估和分析这些数据，对损耗系数的不同定义进行了研究，最后扩展到考虑热方面。此外，应用了已建立的平均局部尾流数据的技术，并特别关注了它们对非绝热情况的适用性。此外，使用了 Amecke 定义的混合平均值的扩展版本，不仅应用了对温度梯度的深远考虑，而且还包含了第三空间维度，以便能够评估除单尾流之外的场遍历横穿。这些技术被应用于在高速叶栅风洞中针对不同工作点和不同叶片温度的特殊测试装置中获得的线性压缩机叶栅的尾流测量数据。可以证明新方法的适用性，并介绍了对结果数据进行空气动力学分析的初始步骤。因此，所获得的技术被证明是评估非绝热条件下压气机和涡轮叶栅上的尾流横切的有力方法。