Design, Development and Experimental Evaluation of Reverse Flow Combustor

A Typical reverse flow combustor is developed for an application in a small gas turbine engine. This is designed for 4 kg/s air flow rate, 6 bar pressure and 1000K exit temperature. This is designed from first principles and fine tuned with Computational Fluid Dynamics (CFD) technique. Combustor is developed and experimentally evaluated in a test rig of Combustion Laboratory of National Aerospace Laboratories (NAL). Inlet to the test rig is compressed dry air at ambient temperature. Combustor performance parameters such as combustion efficiency, total pressure loss and exit temperature pattern factor is presented. Effects of equivalence ratios on these combustion performance parameters are discussed.