Proceedings of 41st Danubia-Adria Symposium Advances in Experimental Mechanics (pp. 83-86)
АУТОР(И) / AUTHOR(S): Nikola Davidović 
, Nenad Kolarević , Milos Stanković , Marko Miloš
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DOI: 10.46793/41DAS2025.083D
УВОД / INTRODUCTION:
Expendable turbojets, typically in thrust range from 40 to 400 daN, are used in target drones and missiles. Because of their usage they are designed to be simple and cheap rather to have some challenged performances according to [1],[2] and [3]. Also, because of their applications they are not requiring rigorous certifications as turbojets for man applications. Usually they are certificated together with the system in which they are installed. This paper is presenting experiences with initial prototype testing. At the moment when designed engine is produced and when some of component or subsystem testing are finished, we have to start with the very first tests. The point is that we will have to check performance of the engine which has to be running for the first time. If everything is fine during the first test and the results are very similar to expecting values it will be perfect. But usually in the engineering world it will not be the case. More than this we have to solve many small issues until we can run the prototype engine with confidence. On the other hand these days time for development is very limited, it is expected that such engine is ready for serial production in 12 to 18 months and consequently it is very important to accurately understand possible problems during initial testing. If we make wrong conclusions it will delay assigned development time and possibly come in position that development went to wrong direction. Technical papers usually describe achieved results but without complete picture of problem which they have to overcome in order to achieve development goals. With such motivation the material discussed at this paper describes what had to done to make prototype engine to run correctly and refers to the turbojet engine TJE-200 at the EDePro company.
КЉУЧНЕ РЕЧИ / KEYWORDS:
ПРОЈЕКАТ / ACKNOWLEDGEMENT:
The presented paper is a result of the researches supported by MPNTR RP according to the contracts 451-03-137/2025-03/ 200105 since 4th February 2025 and 451-03-66/2024-03/200213 since 5th February 2024. The authors wish to acknowledge and thank the company EDePro for the support.
ЛИТЕРАТУРА / REFERENCES:
- D.E.Barbeau (1981) A Family of Small, Low Cost Turbojet Engines for Short Life Applications, ASME 81-GT-205, 198.
- J.F.Rideau, G.Guyader, A.Cloarec (2008) Microturbo Families of Turbojet Engine for Missiles and Uav’s From the TR60 to the New Bypass Turbojet Engine Generation, In 44th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exibit, Hartford, paper no: AIAA 2008- 4590.
- A.Bodemer, Les Turbomachines Aeronautiques Mondiales. Editions Lariviere, 1979.
- Aerospace Structural Metals Handbook, Air Force Material Laboratory, Air Force Systems Command, Wright-Patterson Air Force Base, Ohio, 1971.
- Г.С.Скубачевский, Авиационные газотурбинные двигатели, Машиностроение, Москва 1969.
- R.P.Dengler, L.E.Macioce, Small, low-cost, expendable turbojet engine-I Design, fabrication and preliminary testing. Report, NASA TM X- 3392, 1976.