An account is given of a course of study encompassing the numerous considerations involved in aircraft gas turbine system definition within an aerothermodynamic framework; these considerations range over engine cycle type, air flowpath design, control integration, inlet and exhaust integration, acoustics, survivability, reliability, and mechanical subsystems. The integration of these factors is stressed. The systems approach is employed throughout. Over the years of the course's use, student suggestions have led to a relative deemphasis of the design-related aspects of the subject matter.