Teaching Aero-Engine Performance: From Analytics to Hands-on Exercises Using Gas Turbine Performance Software

Abstract

Abstract In this paper, we present an approach for teaching turbojet engine performance that combines mathematical analysis with the use of gas turbine performance software to provide students with a comprehensive and in-depth understanding of engine performance and how it is affected by design parameter choices. In the first part, we present the derivation of a universally valid analytical model for turbojet engine cycle design, which is the basis of the aircraft propulsion courses at RWTH Aachen University. The analytical model allows for the calculation of specific thrust as well as thermal and propulsive efficiencies as a function of pressure ratios and burner exit temperature. These are all expressed as differentiable functions. Their mathematical extremes form a basis for examining the intricate relationships in turbojet engine design. In the second part, we move from theory to practice. We utilize the GasTurb software for gas turbine performance analysis, computing turbojet engine cycles for a wide range of cycle design parameters, including pressure ratios and burner exit temperatures. The analytically derived trends are validated and errors introduced by simplifications are assessed. Differences between the analytical approach and software-based performance simulations of real engines, like temperature-dependent gas properties and secondary air systems, are emphasized and discussed, thus providing a bridge to real-world applications. In summary, this paper describes a two-step approach to teaching turbojet engine design using analytics and gas turbine performance software. Each approach alone can be used to enrich and extend existing engine performance courses. Combining the approaches has significant benefits, improving understanding and inspiring students to pursue further research in the field of jet engines.