Project Number: 106
Aircraft Technology Innovation
While turbine engines are ubiquitous in propulsion, many of the advances that have been made stem from improvements in component efficiencies rather than system level approaches that quantify the inter-relations of engine operations. This project will create an aero-thermodynamic model of a high-pressure turbine capable of integrating the operational parameters library. This endeavor aims to develop detailed design algorithms, systems of equations, and NPSS code to calculate the necessary turbine operational parameters for a given cycle while interfacing with the experimentally determined library. Turbine efficiency data will be measured from a collaborate research turbine geometry and curated for integration with performance modeling tools. The approach will be refined using an example engine model based on a state-of-the-art engine for calibration purposes.