Gas turbine industry is eager to produce combustion devices that can operate with high efficiency and low emissions. In order to achieve such requirements, the combustion systems need to operate in lean conditions. One of the problems that occur in lean conditions is the rise of combustion instabilities. Instabilities results due to the interaction between heat release and acoustic environment.
In order to address the above problems, a rearward step combustor at laboratory scale is designed that could be used to investigate combustion instabilities. The combustor is capable of operating at elevated pressures and temperatures thus can operate relevant to gas turbine conditions.