Design and Modeling of a Micro Turbojet Engine for UAV Propulsion
G. Jims John Wessley
G. Jims John Wessley, Department of Aerospace Engineering, Karunya Institute of Technology and Sciences, Coimbatore (Tamil Nadu), India.
Manuscript received on 29 May 2019 | Revised Manuscript received on 11 June 2019 | Manuscript Published on 22 June 2019 | PP: 722-726 | Volume-8 Issue-3S, February 2019 | Retrieval Number: C11540283S19/19©BEIESP
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Abstract: This paper presents the design of major components of a turbojet engine that can produce thrust in the range of 4 kN suitable for medium altitude UAV. The paper presents the design and sizing of the turbojet engine components like engine inlet, compressor impeller, compressor diffuser, turbine blades, combustion chamber and its zones as well as the exit nozzle. It is concluded that to develop a thrust of 4 kN, the engine inlet required is 420 mm, while the compressor needs to have a diameter of 250 mm with a turbine of 19 vanes. The combustion chamber length is found to be 259 mm and radius 52 mm while the nozzle exit radius is 125 mm. The paper also presents a detailed estimation of mass of individual components and the total mass of the engine is estimated to be around 46.61 kg. The maximum thrust developed by the engine is found to be 4.4 kN at a rotational speed of 16,540 rpm, which is well above the expected output. Hence, this design can be used for fabrication of Turbojet engine that can develop a maximum of 4 kN thrust required to propel UAVS in the medium altitude range.
Keywords: Design Modeling Components Compressor.
Scope of the Article: Machine Design