Design and Experimentation of a Combustor for High Combustion Intensity

Abstract

The length and volume requirements of small gas turbines for missiles or propelled targets lead to combustor designs with high combustion intensity and large value of the air loading parameter ω The conventional combustors have used conditions corresponding to ω values in the 1 to 10 kg m-3s-1 range. The increase of ω required for combustors in missiles conduces for existing liners to a decrease of combustion efficiency and to an increase of pressure losses. Technical solutions have been worked out to make a combustor operating with a large air loading parameter: (25 kg m-3s-1≤ω≤ 50 kg m3s-1) and a correct combustion efficiency (η = 0.955). Test performed at atmospheric pressure with direct visualization of the combustion zone has shown a uniform primary flame and a moderately heated liner that can withstand short duration flights.