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A detailed dynamic engine simulation of the ABB-GT24/26 gas turbine engine showed a thermal efficiency of πππ»=40.5%. The corresponding measured efficiency for GT-26 was reported as 38.2%. The difference of 2.3% is attributed to numerous failures associated with compressor blade distress in the form of cracking. The failures occurred at the start of the engine operation [19]. This efficiency improvement was achieved despite the following facts: (a) The compressor pressure ratio is far greater than the optimal conventional one (ππππ‘ πΊπ24 β 2 Γ ππππ‘ π΅πΏ) causing the compressor efficiency to decrease. The latter is because of reduced blade height associated with an increase in secondary flow losses. (b) The introduction of a second combustion chamber inherently causes additional total pressure losses. A further efficiency improvement is achieved by eliminating the combustion chambers altogether and placing the combustion process inside the stator blade passages. Figure 9c schematically shows the thermodynamic process of this gas turbine engine, where the combustion is placed inside the stator flow passage of a multi-stage turbine. Starting from the compressor exit pressure, Figure 9c, point 2, fuel is added inside the stator flow passage raising the total temperature, to point 3. The expansion in the stator is followed by the expansion through the first turbine rotor flow passage, point 4. The same expansion processes are repeated in the following turbine stator and rotor blade passages (points 5 through 9). The cross-hatched area refers to the baseline process, whereas the simple-hatched area represents the net work gain which leads to thermal efficiency improvement. Aero-thermodynamic calculations show that for a UHEGT with three stator-internal combustions, a thermal efficiency of above 45% can be achieved. 15PDF Image | DEVELOPMENT OF AN ULTRA-HIGH EFFICIENCY GAS TURBINE ENGINE (UHEGT
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