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temperature distribution for this case. The results show a similar pattern for this configuration and configuration 1 at this scale. But a closer look at the blade surface temperature distribution in the next figure will reveal how much difference the film cooling holes are actually making in bringing down the blade surface temperature. Figure 66 shows the blade surface temperature on stator PS and SS for all different configurations. As shown in this figure, for configuration 1, temperature would go up to 1600 K on the suction side. This temperature is relatively high and requires the blade to be cooled down due to material limitations. In configurations 2 and 3, as shown in the picture, indexing the injectors and the stator blade has led to a significant reduction in the blade surface temperature. The temperature on these surfaces is nearly as low as the compressor air temperature which is ideal for the blade surfaces and completely protects them from the high temperature of the combustion gas. This demonstrates the high effectiveness of the indexing method in order to control the temperature distribution on the blade surfaces. The results for the film cooled blade in configuration 4 are shown in the last part of Figure 66. As shown in this picture, the cooling fluid has successfully brought down the blade surface temperature in all locations. In the areas near the film cooling holes the temperature is dropped significantly, while in the farther areas the temperature drop is relatively lower. Figure 67 shows the film cooling effectiveness (𝜂 = 𝑇∞−𝑇𝑤) contours on stator blade pressure and suction surfaces in configuration 4. As shown 𝑇 −𝑇 in this figure, film cooling effectiveness has its maximum value at about 1 at the exit of each cooling hole. By getting further away from the cooling holes, the values are reduced. The minimum film cooling effectiveness is about 0.1 which takes place on the suction 106 ∞𝑐PDF Image | DEVELOPMENT OF AN ULTRA-HIGH EFFICIENCY GAS TURBINE ENGINE (UHEGT
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