Preliminary Design of a Reverse Flow Annular Combustor and Experimental Investigations at Design and of Design Operating Conditions
Deepa M S1, A Arokkiaswamy2
1Deepa M S, Associate Professor, Department of Aeronautical Engineering, S J C Institute of Technology, Kothanoor (Karnataka), India.
2Dr. A Arokkiaswamy, Professor & Head, Department of Aeronautical Engineering, Dayananda Sagar College of Engineering, Bengaluru (Karnataka), India.
Manuscript received on 23 May 2019 | Revised Manuscript received on 13 June 2019 | Manuscript Published on 27 June 2019 | PP: 247-251 | Volume-8 Issue-1C May 2019 | Retrieval Number: A10440581C19/2019©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: This paper presents design optimization of a Reverse flow annular combustor based on the calculation of geometric parameters, gas temperature profile, liner wall temperatures and position of air admission holes using the preliminary design procedure proposed by Melconian and Modak [1] with Jet A as fuel. It includes fabrication process of the combustion chamber and study of experimental results obtained from the testing of the combustor for temperature distribution at centerline, inlet and outlet of the combustor carried out at design and off design operating conditions for a small gas turbine engine.
Keywords: Reverse Flow Annular Combustor, Preliminary Design, Combustor Test Rig, Experimental Investigations.
Scope of the Article: Machine Design