One dimensional liner temperature prediction in a tubular combustor

Abstract

Liner cooling can be optimized in the preliminary design phase by using one-dimensional heat transfer analysis in scope of the gas turbine combustor liner durability. So it is important to understand heat transfer process in the combustor liner for an effective prediction of liner wall temperatures. In this study, one –dimensional liner wall temperature predictions of an experimental tubular combustor have been performed for different operating conditions. Experimental tests have been obtained by the combustor atmospheric rig tests over a range of inlet temperature from 400 to 475 K and inlet mass flow rates of 0.035–0.050 kg/s at 6 different axial locations representing the primary zone, film cooled area, secondary zone and dilution zone. A tubular type combustor with air-blast fuel injections has been used for the experimental study. By the help of this architecture, it was possible to get more axially symmetrical temperature distribution compared to an annular combustor. Predictions shows that a maximum 85 K error in primary zone. It has been predicted more accurate results in the other zones.