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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Increasing the number of stator internal combustion to 4, raises the efficiency above 47% [15]. A detailed quantitative calculation of each process is presented in Figure 10. In this figure, the compression ratio is increased while the maximum cycle temperature (TIT) is kept constant. These figures represent a comparison between the thermal efficiencies and specific works of baseline GT, the GT24/26, and a UHEGT with three and four stator- internal combustions, UHEGT-3S and UHEGT-4S, respectively. Maximum temperature for all cycles are the same and equal to TIT=1200 C. As shown in Figure 10a, for UHEGT- 3S (with three stator internal combustion stages), a thermal efficiency above 45% is calculated [15]. This exhibits an increase of at least 5% above the efficiency of the most advanced current gas turbine engine, GT24/26. Increasing the number of stator internal combustion to 4, curve labeled with UHEGT-4S, raises the efficiency above 47% which can bring an enormous efficiency increase compared to the existing gas turbine engines. It should be noted that UHEGT-concept requires an optimization of the compressor pressure ratio. As shown in Figure 10a, the optimum pressure ratio for the current UHEGT is around 35 to 40 which is higher than the optimum pressure ratio for a single combustor engine (15-20). Figure 10b shows the specific work comparison for the gas turbines discussed above. Compared to GT-24, UHEGT-technology has about 20% higher specific work, making this technology very suitable for aircraft engines, stand-alone as well as combined cycle power generation applications. This efficiency increase can be established at a compressor pressure ratio of πœ‹π‘ˆπ»πΈπΊπ‘‡ = 35 βˆ’ 40, which can be achieved easily by existing 16

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