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Figure 45. Injector configuration 3: Temperature distribution before and after stator and rotor............................................................................................................70 Figure 46. Injector configuration 3: Temperature distribution at the rotor inlet..............71 Figure 47. Injector configuration 3: Meridional temperature distribution.......................71 Figure 48. Injector configuration 3: Average temperature profile. ..................................72 Figure 49. Injector configuration 3: Average fuel mass fraction profile. ........................73 Figure 50. A sample axial turbine stage (left) with corresponding velocity diagrams (right); (V and W show the absolute and relative velocities, respectively); Reprinted from Ref. [1]. ...................................................................................77 Figure 51. UHEGT thermodynamic cycle: Pressure ratio for compressor and each turbine stage, fuel mass flow rate for each combustion stage, corresponding total power for each component, and the cycle thermal efficiency are shown. ............................................................................................................... 81 Figure 52. Six-stage UHEGT turbine with three stages of stator internal combustion....85 Figure 53. Computational domain for the 3-stage assembly: the domain has 10 total components which include 3 injector rows, 3 stators, 3 rotors, and an inlet extension. .......................................................................................................... 85 Figure 54. Midspan blade loading on the first stator: pressure coefficient distribution on suction and pressure surfaces.......................................................................86 Figure 55. Midspan streamlines in relative frame for the three-stage assembly..............89 Figure 56. Midspan Mach number in relative frame for the three-stage assembly..........90 Figure 57. Midspan static temperature distribution in stage 1. ........................................92 Figure 58. Midspan static temperature distribution in stage 2. ........................................93 Figure 59. Midspan static temperature distribution in stage 3. ........................................94 Figure 60. Temperature distribution at different axial locations: (a) stage 1 rotor inlet, (b) stage 2 rotor inlet, (c) stage 3 rotor inlet, (d) stage 3 exit. ..........................95 Figure 61. Average fuel mass fraction changes with axial location.................................97 Figure 62. Numerical domain for CFD simulation in configuration 1. The injectors’ circumferential locations will be adjusted in configurations 2 and 3. ............101 xviiPDF Image | DEVELOPMENT OF AN ULTRA-HIGH EFFICIENCY GAS TURBINE ENGINE (UHEGT
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