The turbo engines of a supersonic transportpropulsion system require high turbine inlettemperature (TIT) 1700degC and high adiabaticefficiency 90% at high aerodynamic loading. In orderto increase efficiency, several technologies wereapplied to reduce loss and tests in the HPT aerodynamicrig demonstrated that 90% adiabatic efficiency wasachievable. In order to increase cooling performance,film cooling was improved. The results of coolingperformance blade row testing indicated that coolingeffectiveness was sufficient, In the core engine test,at TIT 1700degC measured cooling effectiveness agreedwell with predictions. As a result, advanced designtechnology for high temperature and high loading HPT was demonstrated.
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