Abstract
The combustor that is a 30% flat (rectangular) model of an annular turbojet-engine combustion chamber was studied. It gave a turbulent nonpremixed kerosene-air flame with equivalence ratios within the range of 0.15–0.75. Measurements of CO2 infrared radiation were performed on exhaust gases from a combustor. The infrared radiation images were obtained by an IR camera equipped with a narrow bandpass filter that falls on the CO2 fundamental band. Temperature profiles were measured by the thermocouple at the combustor outlet. The in-house program INFRAD was used to calculate infrared radiation from the CO2 component of the efflux gases from the combustor. The calculation was performed, taking into account the effects of radiation emission and absorption along an optical path. The calculations that allow prediction of “apparent” gas temperatures are those expected to be read by the IR camera. The calculated results are compared with experimental measurements. They are found to be in close agreement.
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