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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compressor set. These values are based on the compressor designed by Widyanto [116]. Further details regarding the compressor simulation model and performance maps can be found in [1] and [30]. Turbine: There are four sets of turbines in the current design: the first three stages which are preceded with injector rows create turbine sets 1 to 3, and the last three stages with conventional gas expansion create turbine set 4. For the turbine, a row-by-row calculation method is used, in which the turbine performance is directly computed based on each stator and rotor row’s geometry. In this method, the geometrical parameters such as mean diameter, blade height, and inlet and exit angles for each stator and rotor row are specified in the input file. Figure 74 shows the schematic representation of consecutive adiabatic turbine stages in row-by-row calculation. As shown in this figure, each stage is decomposed into two rows that are connected with each other via the middle plenum. More details regarding the row-by-row calculation process for turbine can be found in [1]. Injector Rows: In order to model the injector rows in UHEGT, a tubular combustion chamber, shown in Figure 75, is modified. For this purpose, the combustion chamber is scaled down in both axial and radial directions. Two independent scale factors are used in axial and radial directions for each combustion stage. The resulted combustion volume at each stage will be equal to the combustion volume at the corresponding injector row. Figure 76 shows a schematic representation of the injector components in UHEGT used in the current simulations. The combustion volume is calculated based on the length, width, and height of the injector component as shown in the figure. Based on the structure 122

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