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Vaporization behaviour of fuel droplets in a gas turbine combustor

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dc.contributor.author Kouremenos Dimitrios, A en
dc.contributor.author Pantzas Christos, K en
dc.contributor.author Panagakis Georgios, D en
dc.contributor.author Krikkis Rizos, N en
dc.date.accessioned 2014-03-01T02:48:21Z
dc.date.available 2014-03-01T02:48:21Z
dc.date.issued 1995 en
dc.identifier.uri https://dspace.lib.ntua.gr/xmlui/handle/123456789/33751
dc.relation.uri http://www.scopus.com/inward/record.url?eid=2-s2.0-0029425140&partnerID=40&md5=66c465488035a583db4892579c258a7e en
dc.subject.other Carbon dioxide en
dc.subject.other Combustors en
dc.subject.other Evaporation en
dc.subject.other Heat transfer en
dc.subject.other Heating en
dc.subject.other Helicopters en
dc.subject.other Mathematical models en
dc.subject.other Soot en
dc.subject.other Thermodynamic properties en
dc.subject.other Water en
dc.subject.other Droplet trajectories en
dc.subject.other Mie scattering theory en
dc.subject.other Gas turbines en
dc.title Vaporization behaviour of fuel droplets in a gas turbine combustor en
heal.type conferenceItem en
heal.publicationDate 1995 en
heal.abstract A model is developed for the description of the phase change process of evaporation, of droplet particles in a gas turbine engine combustor. The fuel spray is divided into three regimes, the sheet portion, the break up portion and the droplet portion. The sheet region is important in determining the spray cone angle and the initial conditions for the calculation of droplet trajectories. Both convective and radiation mode of heat transfer to the fuel spray due to flame and liner walls are considered. The description of the fuel spray involves, the effects of variable thermophysical properties and of transient heating. In the radiative heat transfer analysis combustion gases comprising both particulates and molecular gases such as CO2, H2O and soot particles which emit, absorb and scatter radiant energy and the full Mie scattering theory is used. The model is applied on a T53-L-13B turboshaft engine used for AB-205 (UH1H) helicopter. en
heal.publisher ASME, New York, NY, United States en
heal.journalName American Society of Mechanical Engineers, Advanced Energy Systems Division (Publication) AES en
dc.identifier.volume 35 en
dc.identifier.spage 261 en
dc.identifier.epage 273 en


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