High pressure test results of a catalytically assisted ceramic combustor for a gas turbine

A catalytically assisted ceramic combustor for a gas turbine was designed t o achieve low NOx emission under 5 ppm at a combustor outlet temperature ov er 1300 degrees C. This combustor is composed of a burner system and a cera mic liner behind the burner system. The burner system consists of 6 catalyt ic combustor segments and 6 premixing nozzles, which are arranged in parall el and alternately. The ceramic liner is made up of the layer of outer meta l wall, ceramic fiber, and inner ceramic tiles. Fuel flow rates for the cat alysts and the premixing nozzles are controlled independently. Catalytic co mbustion temperature is controlled under 1000 degrees C, premixed gas is in jected from the premixing nozzles to the catalytic combustion gas and lean premixed combustion over 1300 degrees C is carried out in the ceramic liner . This system was designed to avoid catalytic deactivation at high temperat ure and thermal and mechanical shock fracture of the honeycomb monolith of the catalyst. A combustor for a 10 MW class, multican type gas turbine was tested under high pressure conditions using LNG fuel. Measurements of emiss ion, temperature, etc. were made to evaluate combustor performance under va rious combustion temperatures and pressures. This paper presents the design features and the test results of this combustor.