Abstract
To cope with the important thermal fluxes which are met in aeronautical combustors, efficient cooling technologies are to be used. In order to calculate the thermal behavior, several methods are available at SNECMA.
As aerodynamics is very complex a satisfactory prediction of the wail temperatures is obtained by wall thermal calculations using boundary conditions coming from 2D or 3D Navier-Stokes calculation of the aerothermal field.
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© 1991 Springer-Verlag Berlin, Heidelberg
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Desaulty, M., Meunier, S. (1991). Heat Transfer Predictions in Aircraft Engines Combustors and Reheats. In: da Graça Carvalho, M., Lockwood, F.C., Taine, J. (eds) Heat Transfer in Radiating and Combusting Systems. EUROTHERM Seminars, vol 17. Springer, Berlin, Heidelberg. https://doi.org/10.1007/978-3-642-84637-3_26
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DOI: https://doi.org/10.1007/978-3-642-84637-3_26
Publisher Name: Springer, Berlin, Heidelberg
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