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contributor authorNiall R. McGlashan
contributor authorPeter R. N. Childs
contributor authorAndrew L. Heyes
date accessioned2017-05-09T00:43:46Z
date available2017-05-09T00:43:46Z
date copyrightMarch, 2011
date issued2011
identifier issn1528-8919
identifier otherJETPEZ-27158#031701_1.pdf
identifier urihttp://yetl.yabesh.ir/yetl/handle/yetl/146067
description abstractA combined cycle gas-turbine generating power and hydrogen is proposed and evaluated. The cycle embodies chemical looping combustion (CLC) and uses a Na based oxygen carrier. In operation, a stoichiometric excess of liquid Na is injected directly into the combustion chamber of a gas-turbine cycle, where it is burnt in compressed O2 produced in an external air separation unit (ASU). The resulting combustion chamber exit stream consists of hot Na vapor and this is expanded in a turbine. Liquid Na2O oxide is also generated in the combustion process but this can be separated, readily, from the Na vapor and collects in a pool at the bottom of the reactor. To regenerate liquid Na from Na2O, and hence complete the chemical loop, a reduction reactor (the reducer) is fed with three streams: the hot Na2O from the oxidizer, the Na vapor (plus some entrained wetness) exiting a Na-turbine, and a stream of solid fuel, which is assumed to be pure carbon for simplicity. The sensible heat content of the liquid Na2O and latent and sensible heat of the Na vapor provide the heat necessary to drive the endothermic reduction reaction and ensure the reducer is externally adiabatic. The exit gas from the reducer consists of almost pure CO, which can be used to generate byproduct H2 using the water-gas shift reaction. A mass and energy balance of the system is conducted assuming reactions reach equilibrium. The analysis allows for losses associated with turbomachinery; heat exchangers are assumed to operate with a finite approach temperature. However, pressure losses in equipment and pipework are assumed negligible—a reasonable assumption for this type of analysis that will still yield meaningful data. The analysis confirms that the combustion chamber exit temperature is limited by both first and second law considerations to a value suitable for a practical gas-turbine. The analysis also shows that the overall efficiency of the cycle, under optimum conditions and taking into account the work necessary to drive the ASU, can exceed 75%.
publisherThe American Society of Mechanical Engineers (ASME)
titleChemical Looping Combustion Using the Direct Combustion of Liquid Metal in a Gas Turbine Based Cycle
typeJournal Paper
journal volume133
journal issue3
journal titleJournal of Engineering for Gas Turbines and Power
identifier doi10.1115/1.4001984
journal fristpage31701
identifier eissn0742-4795
keywordsPressure
keywordsHeat
keywordsTemperature
keywordsCombustion
keywordsVapors
keywordsMetals
keywordsEquilibrium (Physics)
keywordsDesign
keywordsGas turbines
keywordsCycles
keywordsTurbines
keywordsOxygen
keywordsHigh temperature AND Separation (Technology)
treeJournal of Engineering for Gas Turbines and Power:;2011:;volume( 133 ):;issue: 003
contenttypeFulltext


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