Please use this identifier to cite or link to this item: http://nopr.niscair.res.in/handle/123456789/30400
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dc.contributor.authorUnaune, Sunil V-
dc.contributor.authorGanesan, V-
dc.date.accessioned2015-01-19T05:43:32Z-
dc.date.available2015-01-19T05:43:32Z-
dc.date.issued2004-02-
dc.identifier.issn0975-1017 (Online); 0971-4588 (Print)-
dc.identifier.urihttp://hdl.handle.net/123456789/30400-
dc.description31-37en_US
dc.description.abstractIn this paper, reacting flows in an aero-engine afterburner are analyzed using computational fluid dynamics (CFD). A computational procedure is described for calculating the three-dimensional reacting flow fields in a gas turbine afterburner. The computations are based on numerical solution of time-averaged transport equations for mass, momentum, turbulent kinetic energy and dissipation rate using a finite volume formulation. The numerical calculations are performed using SIMPLE(Semi Implicit Method for Pressure Linked Equations). The RNG (Re-normalization Group Theory) k-ɛ model is used for turbulence modeling. Combustion is modeled using PDF (Probability Density Function). The results for air-fuel Ratio of 30 and 46 are obtained and analyzed. en_US
dc.language.isoen_USen_US
dc.publisherNISCAIR-CSIR, Indiaen_US
dc.rights CC Attribution-Noncommercial-No Derivative Works 2.5 Indiaen_US
dc.sourceIJEMS Vol.11(1) [February 2004]en_US
dc.titleAnalysis of reacting flows in an aero-engine afterburner using computational fluid dynamicsen_US
dc.typeArticleen_US
Appears in Collections:IJEMS Vol.11(1) [February 2004]

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