All these engines have a similar structural design. Nowadays, very small turbojet engines with a thrust range of up to 1000 N are used in many applications. Both numerical and experimental investigations are conducted to study the mixing ability of the primary nozzle, the key to optimising the ejector performance.
Ejector nozzles have been developed in combination with special mixer nozzles with the design goal of increasing the pumping performance and thrust augmentation. The secondary mass flow delivered from the ejector nozzle can not only reduce the exhaust gas temperature but also enhance the thrust. The concept of the ejector nozzles offers a solution for further improving the propulsion system following the requirements. But the low overall efficiency, the high exhaust gas temperature and excessive noise emission limit the options for integration and mission profiles.
The special requirements for the design of these propulsion systems include compact installation size, high reliability and low acquisition costs. The examination of small turbojet engines for unmanned aviation systems is a main research activity at the Institute of Aeronautical Engineering at the Universität der Bundeswehr München.
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