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Figure 12. Brown Boveri’s Multi Injection Burner in the GT8 annular combustor; Reprinted from Ref. [9]. ...................................................................................23 Figure 13. EV burner by Alstom; Reprinted from Döbbeling et al. [9]...........................23 Figure 14. Conventional combustion chamber: Typical primary-zone configuration with inlet swirler; Reprinted from Lefebvre [33]. ............................................34 Figure 15. Effects of different parameters on weak extinction limit in a bluff-body stabilized flame using liquid fuel sources: (a) Effect of mainstream velocity, (b) effect of air pressure, (c) effect of inlet flow temperature, (d) effect of approach stream Mach number. ΦWE is weak extinction equivalence ratio, BG and θ are the flame holder blockage and angle, respectively; Reprinted from Refs. [60]-[62]..........................................................................................38 Figure 16. Pressure coefficient distribution along suction and pressure surfaces for the single-stage turbine stator blade. ......................................................................41 Figure 17. Injector configuration 1: cylindrical fuel injectors extended from hub to shroud. ..............................................................................................................42 Figure 18. Injector configuration 1: computational domain. ...........................................42 Figure 19. Single-stage sample turbine with injector configuration 1. ............................43 Figure 20. Injector configuration 2: cylindrical fuel injectors implemented inside the stator blades. .....................................................................................................44 Figure 21. Injector configuration 3: (a) single layer and (b) multilayer vortex generators; (c) gaseous fuel injector in the center of the swirler......................45 Figure 22. Injector configuration 3: computational domain. ...........................................46 Figure 23. Single-stage sample turbine with injector configuration 3. ............................46 Figure 24. Computational grid: (a) structured hexahedral grid over the blade components, (b) boundary layer grid near the blade leading edge, (c) boundary layer grid near the blade trailing edge, (d) tetrahedral elements near the injector surface combined with hexahedral grid in the main domain. .............................................................................................................48 Figure 25. Grid independence study results: velocity and temperature distribution on the midspan line at the exit of stator in configuration 1 for three different grid sizes. ..........................................................................................................49 xvPDF Image | DEVELOPMENT OF AN ULTRA-HIGH EFFICIENCY GAS TURBINE ENGINE (UHEGT
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