Korea Aerospace Research Institute has performed a joint research with the Central Institute of Aviation Motors of Russia on the design, manufacturing, and testing of an annular combustor for a turbo-fan engine with the thrust of 8,000 lbf. In order to reduce smoke generation, a rather large amount of air is introduced to the primary zone. Presented in this paper is a description of the full-scale annular combustor, the test facility, the test procedure, and the test results. The measured parameters include the pressure loss and its dependence on flow velocity, the combustion efficiency by gas analysis, the exit temperature pattern factor for a wide range of air excess ratio, the lean blow-off limit, and the emission characteristics. The main test conditions are the ‘ground idle’ condition and the ‘altitude cruise’ condition. It was confirmed that the exit temperature profile is closely related to the location of dilution holes on the flame tube. Lean blow-off limit is rather narrow since the combustor was designed to provide a large amount of air to the primary zone with an aim of smoke reduction.

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