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    Extinction of hydrogen enriched methane and propane flames through perforated plates flame arrester elements with varying thickness
    (Elsevier BV, 2026-05-27)
    This study investigated the extinction of premixed flames involving methane, propane, hydrogen and air by using a flame arrester element composed of multiple perforated plates. Six stoichiometric mixtures were considered in the experiments, namely, [100%CH4]/air, [25%C3H8+75%H2]/5%He/air, [100%CH4]/10%He/air, [40%C3H8+60%H2]/10%He/air, [75%CH4+25%H2]/air and [10%C3H8+90%H2]/air. Helium was added to three of the mixtures to increase the thermal conductivity and produce different Lewis (Le = 0.72 to 1.36) and Zeldovich numbers (Ze = 4.98 to 8.45). Experiments were performed in a closed duct at 40 kPa and 295 K using flame arrester elements with varying thickness (δplates = 18 to 150 mm) and with orifice diameters of 1.0 and 2.0 mm. The mixtures and arrester configurations were tested at least three times, totaling 240 experiments. A one-dimensional heat-transfer model was also employed to strengthen the interpretation of the experimental observations. The results indicated that mixtures with similar Le and high Ze were successfully extinguished once a sufficiently thick perforated plates assembly was used.
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    Detonation processes application to increase thermal efficiency in gas turbine cycles: Case study for hydrogen enriched fuels
    (Elsevier, 2025)
    This work describes a thermodynamic comparison of the thermal efficiency of gas turbine engines featuring a conventional combustion chamber and a detonation combustion chamber, using methane, ethanol and mixtures of both ethanol and hydrogen and methane and hydrogen as fuels. The composition of gases was determined by the minimization of the Gibbs free energy, whereas temperature, pressure, and velocity of detonation waves were determined by the Chapman-Jouguet theory. The results obtained here show that the DCC gas turbine cycle has a higher net work output and thermal efficiency than the CCC gas turbine cycle for all fuels studied in this work. The maximum thermal efficiency obtained with the DCC gas turbine cycle is indeed 57.22 %, which represents a 53.75 % improvement over the maximum thermal efficiency obtained with the CCC gas turbine cycle (which has a peak thermal efficiency of 37.22 %), under the same pressure ratio and turbine inlet temperature.
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