The Effect of Non-Equilibrium Carbon Monoxide (CO) On Turbine Component Design

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Modern gas turbines engines are designed to deliver high thrust to weight ratios, range, and efficiencies. To get high efficiencies and thrust to weight ratios, the turbine inlet temperature is raised, and the combustor size is reduced. When the turbine inlet is raised above 2000K, dissociated non-equilibrium CO enters the turbine section. If the combustor length is shortened, the fuel has shorter residence time and there is potential for unburnt hydrocarbons leaving the combustor. The dissociated CO and unburnt hydrocarbons react with the oxygen rich film cooling on the turbine nozzle guide vanes and reduce the blade's cooling effectiveness, and life. Therefore, the aim of this project is to study how these reactive species affect the performance of different cooling hole geometries and how to mitigate the effects of heat release from the chemical reactions. A cold shock tube experimental facility at the OTI will be used to study the chemical kinetics and heat transfer in reactive film cooling. The shock produced by the driver gas is used to heat a driven gas seeded with a highly reactive hydrocarbon, which in turn will be blown over a test section with cooling holes ejecting inert and oxygen rich coolants. Optical and non-optical measurement techniques will be used to visualize the reactions and measure the heat transfer and reaction kinetics on the test section. Numerical methods will be used to augment the experimental methodology.