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al. [98]; (3) design and implementation of a cooling system for the stator blades. Showerhead film cooling may be applied to the stator leading edge area. Different approaches in reducing stator blade surface temperature will be further studied in the next section. The main factor that affects the rotor performance is the temperature non- uniformity at the rotor inlet. Figure 60a-c shows the temperature distributions at the inlet of each rotor stage. The Non-Uniformity Index (NUI) defined as (Tmax-Tmin)/Tave is shown for each section. In the calculation of NUI, the thin areas with low temperature near hub and shroud surfaces are excluded. That is because those thin layers are generated intentionally through design to protect the endwalls from the high flame temperature. Based on the results, as the gas moves through the turbine stages, the non-uniformity index may slightly rise. That is due to two reasons: (1) the inlet gas temperatures at the second and third injectors are not fully uniform due to the combustion and incoming non- uniformity from the previous stage. That adds up to the non-uniformity caused by the new injectors which will lead to higher non-uniformity at the next rotor inlet; (2) as the combustion gases pass through rotor, higher density (lower temperature) fluid moves towards the shroud and vice versa. That causes more temperature non-uniformity at the inlet of the next injector which transfers to the rotor inlet. Considering all of the above, the temperature non-uniformity at the inlet of each rotor is quite acceptable. In conventional combustion chambers, the turbine inlet temperature non-uniformity can be up to 40% ([70], [71]) which shows that the current design is performing very well in comparison. Figure 60d shows the temperature distribution at the exit of the third stage. 91PDF Image | DEVELOPMENT OF AN ULTRA-HIGH EFFICIENCY GAS TURBINE ENGINE (UHEGT
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