Experimental and numerical analysis of a small-scale turbojet engine

Since experimental activities on real aeronautical turbines can be very complex and expensive, the use of parts of real engines or small-size turbojets can be very useful for research activities. The present paper describes the results of an experimental and numerical activity that was conducted on a research turbojet engine, with a nominal thrust of 80 N at 80,000 rpm. The aim of the research was to obtain detailed information on the thermodynamic cycle and performance of the engine in order to use it in subsequent activities on the benefits of using alternative fuels in gas turbine engines. A specific characterization of each component of the engine has been performed by means of thermodynamics and CFD analyses and several measured parameters have been critically analyzed and compared with theoretical ones, with the purpose of increasing the knowledge of these kinds of small turbo-engines.