Thermodynamic Performance Analysis of a Micro Turbojet Engine for UAV and Drone Propulsion
Swati Chauhan1, G. Jims John Wessley2
1Swati Chauhan, Department of Aerospace Engineering, Karunya Institute of Technology and Sciences, Coimbatore (Tamil Nadu), India.
2G. Jims John Wessley, Department of Aerospace Engineering, Karunya Institute of Technology and Sciences, Coimbatore (Tamil Nadu), India.
Manuscript received on 22 April 2019 | Revised Manuscript received on 01 May 2019 | Manuscript Published on 08 May 2019 | PP: 1-6 | Volume-7 Issue-5S3 February 2019 | Retrieval Number: E11000275S19/19©BEIESP
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© The Authors. Blue Eyes Intelligence Engineering and Sciences Publication (BEIESP). This is an open access article under the CC-BY-NC-ND license (http://creativecommons.org/licenses/by-nc-nd/4.0/)
Abstract: A thermodynamic performance analysis of a single spool micro turbojet engine that can produce thrust to a maximum of 4 kN is performed using Gas Turbine Simulation Programme (GSP). There is a huge gap in the availability of micro gas turbine engines in the thrust range of 0.13 to 4.45 kN to power UAVs and drones. This analysis brings out the feasibility of thrust generation in a micro turbojet engine so as to fill the gap. The engine is analyzed for four different mass flow rates, Mach numbers ranging from 0.3 to 0.9 with the operating altitude between 5000 m to 9000 m. The nett thrust produced for a pressure range of 2.5 and is in the range of 3.9 to 4 kN at a mass flow rate of 7.6 kg/s which satisfies the expected design requirement of the engine. Also, the maximum turbine inlet temperature is less than 1000 K so that there is no need for a new material required in the combustor and turbine where the high temperaure exists. The outcomes of this analysis form a strong base for further analysis, design and fabrication of micro gas turbine engines to propel future UAVs and drones.
Keywords: Micro Performance Analysis Programme.
Scope of the Article: Microwave Filter