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DEVELOPMENT OF AN ULTRA-HIGH EFFICIENCY GAS TURBINE ENGINE (UHEGT

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DEVELOPMENT OF AN ULTRA-HIGH EFFICIENCY GAS TURBINE ENGINE (UHEGT ( development-an-ultra-high-efficiency-gas-turbine-engine-uheg )

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the stator and rotor blades at hub, mean, and tip sections. After that, standard base profiles are superimposed on each camberline to generate suction and pressure surfaces. The maximum thickness increases 20% from tip to hub in each blade in order to overcome the higher torque near the hub. The profiles at hub, mean and tip sections are imported into SolidWorks. The 3D model of each blade is generated and all components are assembled together. Figure 52 shows the cross section of the six-stage turbine with three stages of stator internal combustion. The numerical domain generated for the CFD simulation is shown in Figure 53. This domain represents the first three stages of the system which includes 3 injector rows, 3 stators, 3 rotors, and an inlet extension. Periodic boundary conditions are used in each component in order to bring down the size of the computational domain to include only one blade and its corresponding injectors at each row. The design of the injectors is based on the single stage simulations which will be discussed in the next section. The mesh generation process, numerical method and boundary conditions are similar to the single stage turbine described in the previous chapter. The total number of elements for the computational domain of the 3-stage assembly is more than 25 m. For further details, please refer to the sections IV.4 and IV.5. V.4. Results and Discussion Figure 54 shows the blade loading (static pressure coefficient distribution, 𝐢𝑃 = π‘ƒβˆ’π‘ƒπ‘ π‘‘π‘Žπ‘”) over the first stator’s suction and pressure surfaces. This diagram shows a high amount of pressure difference between the suction and pressure surfaces which means a 84 1πœŒπ‘‰2 2

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