The use of drones as unmanned aerial vehicles for private as well as commercial use is becoming increasingly important. Various technologies are available for the propulsion of a drone, with their specific advantages and disadvantages: Electric motor, combustion engine, gas turbine. At least in terms of torque versus speed and vibration, the gas turbine offers significant advantages over the combustion engine. In addition, the comparatively high weight of electric motors and batteries has a negative effect in every aviation application. A rough exploration of the market for small gas turbines revealed that no shaft power engines are available in the 20 to 40 kW power range, while jet engines are available for higher powers. As part of the FFG-funded exploratory project "JET2SHAFT", an existing jet engine was therefore converted into a turboshaft engine for the required power range under the TAKE OFF funding program. The project includes a circular process calculation for determining the boundary conditions of the required power turbine in the required power range, as well as an analytical prediction of the single-stage axial turbine. Furthermore, the airfoil shapes of the runner and guide vane series as well as the blade numbers were optimized with regard to loss minimization by means of CFD support. The analytical design also includes a structural-mechanical and structural-dynamic calculation of the power turbine, the results of which were compared with a numerical modal analysis and a static strength calculation using finite elements (FEM).