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- Carcasci, Carlo, 1968, et al.
(author)
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Design issues performance of a chemically recuperated aeroderivative gas turbine
- 1998
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In: Proceedings of the Institution of Mechanical Engineers, Part A: Journal of Power and Energy. - : SAGE Publications. - 0957-6509 .- 2041-2967. ; 212:5, s. 315-329
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Journal article (peer-reviewed)abstract
- A number of innovative gas turbine cycles have been proposed lately, including the humid air turbine (HAT) and the chemically recuperated gas turbine (CRGT). The potential of the CRGT cycle lies in the ability to generate power with a high efficiency and ultra-low NOx emissions. Much of the research work published on the CRGT cycle is restricted to an analysis of the thermodynamic potential of the cycle. However, little work has been devoted to discussion of some of the relevant design and operation issues of such cycles. In this paper, part-load performance characteristics are presented for a CRGT cycle based on an aeroderivative gas turbine engine adapted for chemical recuperation. The paper also includes discussion of some of the design issues for the methane-steam reformer component of the cycle. The results of this study show that large heat exchange surface areas and catalyst volumes are necessary to ensure sufficient methane conversion in the methane steam reformer section of the cycle. The paper also shows that a chemically recuperated aeroderivative gas turbine has similar part-load performance characteristics compared with the corresponding steam-injected gas turbine (STIG) cycle.
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- Carcasci, Carlo, 1968, et al.
(author)
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Modular approach to analysis of chemically recuperated gas turbine cycles
- 1998
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In: Presented at the International Gas and Turbine & Aeroengine Congress & Exhibition Stockholm, Sweden, June 2-June 5, 1998. - 1103-2952.
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Conference paper (peer-reviewed)abstract
- Current research programmes such as the CAGT programme investigate the opportunity for advanced power generation cycles based on state-of-the-art aeroderivative gas turbine technology. Such cycles would be primarily aimed at intermediate duty applications. Compared to industrial gas turbines, aeroderivatives offer high simple cycle efficiency, and the capability to start quickly and frequently without a significant maintenance cost penalty. A key element for high system performance is the development of improved heat recovery systems, leading to advanced cycles such as the humid air turbine (HAT) cycle, the chemically recuperated gas turbine (CRGT) cycle and the Kalina combined cycle. When used in combination with advanced technologies and components, screening studies conducted by research programmes such as the CAGT programme predict that such advanced cycles could theoretically lead to net cycle efficiencies exceeding 60%. In this paper, the authors present the application of the modular approach to cycle simulation and performance predictions of CRGT cycles. The paper first presents the modular simulation code concept and the main characteristics of CRGT cycles. The paper next discusses the development of the methane–steam reformer unit model used for the simulations. The modular code is then used to compute performance characteristics of a simple CRGT cycle and a reheat CRGT cycle, both based on the General Electric LM6000 aeroderivative gas turbine.
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- Godin, Thierry, et al.
(author)
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Theoretical analysis of environmental and energetic performance of very high temperature turbo-jet engines
- 1999
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In: national Journal of Thermal Sciences. ; 38:5, s. 442-451
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Journal article (peer-reviewed)abstract
- Current progress in gas turbine performance is achieved mainly by increasing the turbine inlet temperature. State of-the-art military aircraft gas turbines operate with turbine inlet temperatures exceeding 2 000 K, and future development plans call for even higher temperature levels. At such high temperatures, the hot combustion gases can no longer be considered as chemically inert, and it becomes important to account for the chemically reactive nature of the expanding flow. In this paper, the authors present a one-dimensional model of the chemically reactive flow through the first turbine stage of an aircraft turbo-jet engine. The model is used to study the impact of chemical reactivity on pollutant emission characteristics and engines performance (i.e. overall efficiency and specific thrust). Three different casess are considered: sea-level static operation (take-off), commercial aircraft in subsonic cruising at 10 000 m altitude, and military aircraft in supersonic flight at 20 000 m altitude. The results of this study show, for instance, that the production of environmental pollutants in the turbine as a result of chemical reactivity is particularly significant for turbo-jets operating at subsonic cruise velocities. Moreover, in both flight conditions considered, the increase of operating temperature decreases the overall efficiency.
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