Aerothermal optimisation of late suction surface cooling for high-pressure nozzle guide vanes

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Increasing the turbine entry temperature in a jet engine increases the cycle efficiency. High-pressure nozzle guide vanes are exposed to temperatures above their melting points. Film cooling is used to reduce the metal temperature of high-pressure nozzle guide vanes and increase vane life. Film cooling is often omitted from the suction surface due to high losses associated with coolant injection. There are few studies in the literature that quantify the mass flow, aerodynamic loss and metal effectiveness effects associated with late suction surface film cooling. This project aims to develop new analytical models, numerical tools and experimental techniques to predict these effects and propose an optimal suction surface film cooling design.One-dimensional analytical models will be developed to predict aerodynamic loss as a function of cooling hole surface distance. Analytical models will also be used to predict mass flow changes associated with coolant injection. Heat transfer models will be developed to study the additive effects of multiple cooling holes on metal effectiveness. Three-dimensional numerical studies are planned on existing and new cooling hole geometries. The ECAT facility at the University of Oxford will be used to conduct high-accuracy temperature and mass flow measurements. Experimental data and analytical predictions will be compared.