Design of a Micro-Turbojet

This manuscript describes the design of a 220-newton student-built micro-turbojet. The design process encompasses the comprehensive design of all major components and systems of a turbojet engine, including the compressor, combustor, turbine, rotordynamics, integration, and startup. The engine consists of a single-stage centrifugal compressor, an annular combustor, and a single-stage axial turbine. Gaseous propane is the fuel of choice for initial testing. Each section describes the process used to design one major component or system and includes preliminary design considerations, detailed analysis of design choices, and the final design outcomes. Included are outlines of the planned manufacturing methods, an overview of instrumentation, and considerations for test stand integration.