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Table 4. Comparison between turbine stage power productions calculated by 2D and CFD simulations Stage 1 Stage 2 Stage 3 2D design power (MW) 23.7 26.0 32.5 CFD calculated power (MW) 21.5 23.6 34.9 Difference (%) -9.3 -9.2 +7.4 Table 5. Total pressure loss values in the injector rows Total pressure loss (%) Injector row 1 0.8 Injector row 2 1.9 Injector row 3 2.5 those regions are larger because of lower mainstream pressure. The total pressure loss in all of the three injector components is about 5% which is an acceptable value in comparison with conventional combustion chambers. Figure 61 shows the average fuel mass fraction in terms of the axial (streamwise) location. As shown in this figure, the fuel particles burn immediately after they are injected into the domain. So the fuel mass fraction goes to near 0% before the flow has reached the stator LE. This provides a proper space for the hot gas to mix with the mainstream flow along the stator channel. When the combustion gas reaches the rotor, the mixture has reached a relatively uniform temperature distribution which provides a proper working environment for rotor. NOx emission at the system exit is 107 ppmv. Considering the high load of the system and multiple steps of fuel injection, and based on the regulated standard emissions (mentioned in [92]), and also in comparison with other studies (Kroniger et al. [99]), the NOx emission of the current system is completely in the acceptable range. 96PDF Image | DEVELOPMENT OF AN ULTRA-HIGH EFFICIENCY GAS TURBINE ENGINE (UHEGT
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