22nd Congress of International Council of the Aeronautical Sciences, Harrogate, UK, 28 August - 1st September, 2000
Paper ICAS 2000-5.5.2

COMPUTER PROGRAM FOR SIMPLIFIED EVALUATION OF GAS RADIATION IN TURBINE ENGINE ENCLOSURES

T. Rodríguez, L. M. Rodríguez
ITP Accessories & Systems Group

Keywords: gas radiation, turbine engine, computer evaluation

Gas radiation is an important heat input to the walls exposed to an afterburning process in a turbojet engine, specially if they are submitted to film cooling or if gas convection is not important on their surface. Hence, it is necessary to take into account this kind of heat in the thermal analysis of the engine components implied. Some commercial software packages for thermal analysis are able to evaluate radiation heat transfer from solid surfaces. However, there is not a commercial software available which is capable of calculating radiation heat transfer from a gas volume, and less so when a luminous gas is involved in the process. On the other hand, the study of gas radiation is a complex and expensive subject because of the amount of factors on which the gas radiation properties depend (shape of gas volume, wavelength, emission of soot particles formed because of incomplete combustion, directional properties of emission and absorption…). The aim of this work is to present a computer program that uses a simplified approach to evaluate the radiation heat fluxes incident on the walls exposed to a hot luminous gas, and its application to the thermal analysis of a military turbojet thrust augmentor.

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