The Experts below are selected from a list of 15582 Experts worldwide ranked by ideXlab platform
K. Choudhary - One of the best experts on this subject based on the ideXlab platform.
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Exergy analysis of the regenerative Gas Turbine Cycle using absorption inlet cooling and evaporative aftercooling
Journal of The Energy Institute, 2009Co-Authors: Abdul Khaliq, K. ChoudharyAbstract:AbstractThis paper provides an exergy analysis to investigate the effects of pressure ratio, Turbine inlet temperature, compressor inlet temperature and ambient relative humidity on the thermodynamic performance of a regenerative Gas Turbine Cycle using absorption inlet cooling and evaporative aftercooling. Combined first and second law analysis indicates that the exergy destruction in various components of the Gas Turbine Cycle is significantly affected by compressor pressure ratio and Turbine inlet temperature, and slightly varies with the compressor inlet temperature and ambient relative humidity. It also indicates that the maximum exergy destroyed in the combustion chamber; which represents over 60% of the total exergy destruction in the overall system. The net work output, first law efficiency, and second law efficiency of the Cycle significantly varies with the change in the pressure ratio, Turbine inlet temperature, compressor inlet temperature and ambient relative humidity.
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thermodynamic performance assessment of an indirect intercooled reheat regenerative Gas Turbine Cycle with inlet air cooling and evaporative aftercooling of the compressor discharge
International Journal of Energy Research, 2006Co-Authors: Abdul Khaliq, K. ChoudharyAbstract:This study provides a computational analysis to investigate the effects of Cycle pressure ratio, Turbine inlet temperature (TIT), and ambient relative humidity (φ) on the thermodynamic performance of an indirect intercooled reheat regenerative Gas Turbine Cycle with indirect evaporative cooling of the inlet air and evaporative aftercooling of the compressor discharge. Combined first and second-law analysis indicates that the exergy destruction in various components of Gas Turbine Cycles is significantly affected by compressor pressure ratio and Turbine inlet temperature, and is not at all affected by ambient relative humidity. It also indicates that the maximum exergy is destroyed in the combustion chamber; which represents over 60% of the total exergy destruction in the overall system. The net work output, first-law efficiency, and the second-law efficiency of the Cycle significantly varies with the change in the pressure ratio, Turbine inlet temperature and ambient relative humidity. Results clearly shows that performance evaluation based on first-law analysis alone is not adequate, and hence more meaningful evaluation must include second-law analysis. Decision makers should find the methodology contained in this paper useful in the comparison and selection of Gas Turbine systems. Copyright © 2006 John Wiley & Sons, Ltd.
A M Bassily - One of the best experts on this subject based on the ideXlab platform.
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Performance improvements of the recuperated Gas Turbine Cycle using absorption inlet cooling and evaporative aftercooling
Proceedings of the Institution of Mechanical Engineers Part A: Journal of Power and Energy, 2002Co-Authors: A M BassilyAbstract:An absorption inlet cooling system is introduced into the recuperated Gas Turbine Cycle. The exhaust Gases of the Cycle are used to run the system. Five different layouts of the recuperated Gas Turbine Cycle are presented. These include the effects of absorption inlet cooling, evaporative inlet cooling and evaporative cooling of compressor discharge (evaporative aftercooling), and the combined effect of absorption inlet cooling and evaporative aftercooling. A parametric study of the effect of pressure ratio, ambient temperature and relative humidity on the performance of all Cycles is carried out. The results indicate that absorption inlet cooling could increase the efficiency of the recuperated Cycle by up to 4 per cent, compared with 2.2 per cent for evaporative inlet cooling. Absorption inlet cooling with evaporative aftercooling could increase the optimum per efficiency of the recuperated Cycle by up to 5 per cent and its maximum power by up to 65 per cent. Evaporative aftercooling reduces the impact of inlet cooling. Another parametric study of the effect of the Turbine compressor inlet temperature ratio on the optimum pressure ratios indicated that Cycles with evaporative aftercooling have higher optimum pressure ratios, which could be a function of the inlet temperature ratio and air temperature at the compressor outlet.
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Effects of evaporative inlet and aftercooling on the recuperated Gas Turbine Cycle
Applied Thermal Engineering, 2001Co-Authors: A M BassilyAbstract:Inlet air cooling and cooling of the compressor discharge using water injection boost both efficiency and power of Gas Turbine Cycles. Four different layouts of the recuperated Gas Turbine Cycle are presented. Those layouts include the effect of evaporative inlet and aftercooling (evaporative cooling of the compressor discharge). A parametric study of the effect of Turbine inlet temperature (TIT), ambient temperature, and relative humidity on the performance of all four layouts is investigated. The results indicate that as TIT increases the optimum pressure ratio increases by 0.45 per 100 K for the regular recuperated Cycle and by 1.4 per 100 K for the recuperated Cycle with evaporative aftercooling. The Cycles with evaporative aftercooling have distinctive pattern of performance curves and higher values of optimum pressure ratios. The results also showed that evaporative cooling of the inlet air could boost the efficiency by up to 3.2% and that evaporative aftercooling could increase the power by up to about 110% and Cycle efficiency by up to 16%.
Abdul Khaliq - One of the best experts on this subject based on the ideXlab platform.
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Exergy analysis of the regenerative Gas Turbine Cycle using absorption inlet cooling and evaporative aftercooling
Journal of The Energy Institute, 2009Co-Authors: Abdul Khaliq, K. ChoudharyAbstract:AbstractThis paper provides an exergy analysis to investigate the effects of pressure ratio, Turbine inlet temperature, compressor inlet temperature and ambient relative humidity on the thermodynamic performance of a regenerative Gas Turbine Cycle using absorption inlet cooling and evaporative aftercooling. Combined first and second law analysis indicates that the exergy destruction in various components of the Gas Turbine Cycle is significantly affected by compressor pressure ratio and Turbine inlet temperature, and slightly varies with the compressor inlet temperature and ambient relative humidity. It also indicates that the maximum exergy destroyed in the combustion chamber; which represents over 60% of the total exergy destruction in the overall system. The net work output, first law efficiency, and second law efficiency of the Cycle significantly varies with the change in the pressure ratio, Turbine inlet temperature, compressor inlet temperature and ambient relative humidity.
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thermodynamic performance assessment of an indirect intercooled reheat regenerative Gas Turbine Cycle with inlet air cooling and evaporative aftercooling of the compressor discharge
International Journal of Energy Research, 2006Co-Authors: Abdul Khaliq, K. ChoudharyAbstract:This study provides a computational analysis to investigate the effects of Cycle pressure ratio, Turbine inlet temperature (TIT), and ambient relative humidity (φ) on the thermodynamic performance of an indirect intercooled reheat regenerative Gas Turbine Cycle with indirect evaporative cooling of the inlet air and evaporative aftercooling of the compressor discharge. Combined first and second-law analysis indicates that the exergy destruction in various components of Gas Turbine Cycles is significantly affected by compressor pressure ratio and Turbine inlet temperature, and is not at all affected by ambient relative humidity. It also indicates that the maximum exergy is destroyed in the combustion chamber; which represents over 60% of the total exergy destruction in the overall system. The net work output, first-law efficiency, and the second-law efficiency of the Cycle significantly varies with the change in the pressure ratio, Turbine inlet temperature and ambient relative humidity. Results clearly shows that performance evaluation based on first-law analysis alone is not adequate, and hence more meaningful evaluation must include second-law analysis. Decision makers should find the methodology contained in this paper useful in the comparison and selection of Gas Turbine systems. Copyright © 2006 John Wiley & Sons, Ltd.
Joachim Kurzke - One of the best experts on this subject based on the ideXlab platform.
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Gas Turbine Cycle Design Methodology: A Comparison of Parameter Variation With Numerical Optimization
Journal of Engineering for Gas Turbines and Power, 1999Co-Authors: Joachim KurzkeAbstract:In Gas Turbine performance simulations often the following question arises : what is the best thermodynamic Cycle design point? This is an optimization task which can be attacked in two ways. One can do a series of parameter variations and pick from the resulting graphs the best solution or one can employ numerical optimization algorithms that produce a single Cycle that fulfills all constraints. The conventional parameter study builds strongly on the engineering judgement and gives useful information over a range of parameter selections. However, when values for more than a few variables have to be determined while several constraints are existing, then numerical optimization routines can help to find the mathematical optimum faster and more accurately. Sometimes even an outstanding solution is found which was overlooked while doing a preliminary parameter study. For any simulation task a sophisticated graphical user interface is of great benefit. This is especially true for automated numerical optimizations. It is quite helpful to see on the screen of a PC how the variables are changing and which constraints are limiting the design. A quick and clear graphical representation of trade studies is also of great advantage. The paper describes how numerical optimization and parameter studies are implemented in a Windows-based PC program. As an example, the Cycle selection of a derivative turbofan engine with a given core shows the merits of numerical optimization. The parameter variation is best suited for presenting the sensitivity of the result in the neighborhood of the optimum Cycle design point.
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Gas Turbine Cycle Design Methodology: A Comparison of Parameter Variation With Numerical Optimization
Volume 2: Aircraft Engine; Marine; Microturbines and Small Turbomachinery, 1998Co-Authors: Joachim KurzkeAbstract:In Gas Turbine performance simulations often the question arises: What is the best thermodynamic Cycle design point? This is an optimization task which can be attacked in two ways: One can do a series of parameter variations and pick from the resulting graphs the best solution or one can employ numerical optimization algorithms that produce a single Cycle which fulfills all constraints.The conventional parameter study builds strongly on the engineering judgement and gives useful information over a range of parameter selections. However, when values for more than a few variables have to be determined while several constraints are existing, then numerical optimization routines can help to find the mathematical optimum faster and more accurately. Sometimes even an outstanding solution is found which was overlooked while doing a preliminary parameter study.For any simulation task a sophisticated graphical user interface is of great benefit. This is especially true for automated numerical optimizations. It is quite helpful to see on the screen of a PC how the variables are changing and which constraints are limiting the design. A quick and clear graphical representation of trade studies is also of great advantage. The paper describes how numerical optimization and parameter studies are implemented in a Windows-based PC program.As an example, the Cycle selection of a derivative turbofan engine with a given core shows the merits of numerical optimization. The parameter variation is best suited for presenting the sensitivity of the result in the neighborhood of the optimum Cycle design point.Copyright © 1998 by ASME
Ali Koç - One of the best experts on this subject based on the ideXlab platform.
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Analysing the performance, fuel cost and emission parameters of the 50 MW simple and recuperative Gas Turbine Cycles using natural Gas and hydrogen as fuel
International Journal of Hydrogen Energy, 2020Co-Authors: Yıldız Koç, Hüseyin Yağlı, Adnan Görgülü, Ali KoçAbstract:Abstract In the present study, firstly, the power production, thermal and exergy efficiencies were calculated for the simple and recuperative Gas Turbine Cycles at constant power production (50 MW) and Turbine outlet temperature (450 °C). The system was analysed for the cases of using both natural Gas and pure hydrogen as a fuel for simple and recuperative Gas Turbine systems. After analyses, the efficiencies of the recuperative Gas Turbine Cycle were higher than the simple Gas Turbine Cycle up to 18 bar pressure for both natural Gas and H2. At the pressure of 18 bar and above, the efficiency of the simple Gas Turbine Cycle found higher than the recuperative Gas Turbine Cycle since the compressor outlet temperature is higher than the Turbine outlet temperature. Despite the higher cost of H2 for unit power production, the H2 used Gas Turbine Cycles has more advantageous than natural Gas in terms of performance, environment and CO2 emission. For the cases of using H2 and natural Gas as fuel, the minimum fuel cost was calculated as 0.345 $/kWh and 0.075 $/kWh at 20 bar for simple Gas Turbine Cycle, while they were found as 0.322 $/kWh and 0.071 $/kWh at 4 bar for recuperative Gas Turbine Cycle, respectively. The CO2 emission of the 50 MW Gas Turbine was found between 46.27 tones-CO2/h and 71.15 tones-CO2/h for natural Gas using simple and recuperative Gas Turbine systems, besides zero CO2 emission of using H2.
