Parametric Analysis of a Dual Combustion Ramjet Engine
G. Jims John Wessley1, Shilpa Pradeep2
1G. Jims John Wessley, Department of Aerospace Engineering, Karunya Institute of Technology and Sciences, Coimbatore (Tamil Nadu), India.
2Shilpa Pradeep, Department of Aerospace Engineering, Karunya Institute of Technology and Sciences, Coimbatore (Tamil Nadu), India.
Manuscript received on 23 April 2019 | Revised Manuscript received on 05 May 2019 | Manuscript Published on 17 May 2019 | PP: 130-135 | Volume-7 Issue-6S4 April 2019 | Retrieval Number: F10250476S419/2019©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: The Dual Combustion Ramjet (DCR) engine is capable of economically generating thrust at both supersonic and hypersonic velocities with reasonable safety so as to make them potential alternatives for rocket engines used during atmospheric stage of flight. A preliminary analysis of a DCR engine at various velocities, altitude and equivalence ratios are performed and the results are presented in this paper. The paper presents the variation of thrust, specific impulse and overall efficiency at various inputs of Mach varying from 3 to 7, Equivalence ratio 0.3 to 1, altitudes 20,000 feet to 50,000 feet and inlet diameter from 200mm to 400mm. The thrust increases with increase in Mach number of the flow and inlet area and decreases with increase in altitude and equivalence ratio. The specific impulse of the engine decreases with equivalence ratio for low Mach numbers and increases for higher Mach numbers. It is also found from the analysis that the engine is capable of producing a thrust of 14.25 kN with an overall efficiency of 44% while operating at Mach 7 with an equivalent ratio of 0.3 at an altitude of 15, 240 m (50,000 ft). The results are encouraging and substantiate the claim that these engines can play a major role in the future propulsion and space exploration.
Keywords: Ramjet, Dual Combustion, Supersonic, Equivalence Ratio, Thrust.
Scope of the Article: Aerospace Engineering