Turbojets offer high power density and low mechanical complexity, enabling compact and lightweight propulsion systems well suited for high-speed, space-constrained applications such as UAVs, missiles and other attritional airframes. However, as single-stream engines, turbojets exhibit inherently lower propulsive efficiency than turbofans, placing greater importance on aerodynamic design quality and component-level performance.
Within this work, a compressor–turbine pair is developed to meet specified thrust and turbine inlet temperature targets representative of a high-speed drone application, based on industryderived requirements. A Brayton-cycle-based analysis first defines the component-level design requirements, which are then refined through manual iteration. Parametric geometry is generated and adjusted within CFturbo and coupled with external CFD and optimization tools for performance evaluation and design space exploration.
