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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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unknown parameters (α3, β2, β3 and r) are calculated by solving the equation set of 5.2a-d. In this process, we tried to distribute the stage load coefficients, λ, properly over different stages. To achieve this goal, the initial assumptions are modified in a trial and error process until the desired values are acquired. Finally, in order to maintain radial equilibrium from hub to shroud, the free vortex flow equation is applied as described in [1]. In this process, after calculation of all the stage parameters at the mean diameter, the free vortex law is applied at hub and shroud sections to calculate the corresponding blade angles. All of the stage design and calculation processes are performed in an in-house FORTRAN code developed for this study (Appendix A). V.2. Cycle Design As the system is designed to use natural gas as the main source of fuel, the thermodynamic cycle is based on the methane air mixture. A 3-stage combustion process is considered for the current design. It provides enough room for reheat while not making the system too complicated. The process starts at near atmospheric pressure and temperature. Based on the previous and current calculations, and as shown in Figure 10a, the optimum compressor pressure ratio for a 3-stage combustion UHEGT is around 40:1. So, the compressor is set up as one unit with the pressure ratio of 40:1 and an estimated isentropic efficiency of 90%. The next design factor is the turbine inlet temperature. In the Brayton cycle (which describes the process in conventional gas turbines), increasing the TIT leads to an increase in the cycle efficiency. But on the other hand, a higher TIT requires a higher amount of cooling air and a more complicated cooling system which can 79

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