Experimental investigations of mainstream turbulence intensity (Tu) effect on conjugate heat transfer performances, total pressure loss and solid thermal deformations of vane laminated cooling end-walls (LCEs) have been carried out under two engine-near mainstream-to-coolant temperature ratios of 1.4 and 2.0. Influences of parameters of internal elements of LCEs were discussed. A servicing film cooling end-wall (FCE) was chosen as a reference. Two typical Tus were designed, 2.2% and 10.1% (in the engine range). Measurements of fluid-thermal-solid coupling characteristics of cooled end-walls were implemented in a hot wind tunnel based on matched engine Biot number under three mass flow ratios. Generally, the elevated Tu exhibited a negative influence on overall cooling effectiveness and component reliability of cooled end-walls, total pressure loss in cascade and slight thermal deformations of LCEs. Moreover, the elevated Tu displayed a negative effect on the remarkable benefit of LCEs over FCE. The shape and diameter of pin-fins and the impingement-hole size played complex roles on overall effectiveness, surface thermal gradient, aerodynamic loss and component weight. However, the Tu effect on the aforementioned roles was slight. Overall, the LCE with diamond-shaped pin-fins and large impingement-holes was the most optimal design.

主流湍流强度（Tu）对叶片叠层冷却端壁（LCE）的共轭传热性能，总压力损失和固体热变形的影响的实验研究是在两个发动机接近的主流与冷却剂的温度比为的情况下进行的。 1.4和2.0。讨论了LCE内部元素参数的影响。选择维修膜冷却端壁（FCE）作为参考。设计了两种典型的Tu s，分别为2.2％和10.1％（在发动机范围内）。在匹配的发动机Biot数下，在三种质量流量比的基础上，在热风洞中对冷却端壁的流固耦合特性进行了测量。通常，升高的涂对冷却端壁的整体冷却效率和组件可靠性，级联中的总压力损失以及LCE的轻微热变形产生不利影响。此外，Tu含量升高对LCE优于FCE的显着好处表现出负面影响。针状翅片的形状和直径以及冲击孔的尺寸在总体有效性，表面热梯度，空气动力学损失和部件重量方面起着复杂的作用。但是，涂对上述作用的影响很小。总体而言，具有菱形针状鳍片和较大冲击孔的LCE是最佳设计。