Computational Investigation on Design of Scramjet Combustor – A Review
Kumari Ambe Verma1, K. M. Pandey2, K. K. Sharma3
1Kumari Ambe Verma, Research Scholar, Department of Mechanical Engineering, National Institute of Technology, Silchar (Assam), India.
2K. M. Pandey, Professor, Department of Mechanical Engineering, National Institute of Technology, Silchar, (Assam), India.
3K. K. Sharma, Associate Professor, Department of Mechanical Engineering, National Institute of Technology, Silchar, (Assam), India.
Manuscript received on 24 March 2019 | Revised Manuscript received on 05 April 2019 | Manuscript Published on 18 April 2019 | PP: 544-548 | Volume-7 Issue-6S March 2019 | Retrieval Number: F03050376S19/2019©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: Supersonic combustion is carried out primarily in air breathing engines. Atmospheric air is used as an oxidizer and fuel are commonly stored within the system. No moving parts are available in the scramjet engine, which gives higher thrust to weight ratio compared with any other propulsion engines. Different techniques and approaches are used for getting better results in the form of improved mixing, momentum, drag etc. The problems present in the combustor can easily be identified with the help of boundary layer parameters. Small improvement can lead to better performance. One of the technique is by using vortex generator. It creates vortices in the lateral plane. Turbulence can also be generated with the help of wedges, ramp, pylon etc., inside the combustion chamber. So the review article is focused entirely on the effects of boundary layer performance parameters due to implementation of vortex generator in the supersonic combustion ramjet engine (scramjet) at different locations with variable sizes. Basic principle behind use of vortex generator is the vortex formation in the downstream to overcome separation and drag. Geometrical shape is a major concern on vortices formation, so different kind of geometrical shapes have been taken for study such as standard micro ramp, dissymmetric micro ramp, slotted micro ramp, cantilevered micro ramp, swept micro ramp, unswept micro ramp, micro vanes, pylon and ramped vane type of vortex generators. To summarize the entire literature review. It is seen from the literature review that standard micro ramp can help in improving momentum deficits and drag however slotted micro ramp can improve mixing performance. Ramped vane vortex generator gives overall performance of boundary layer in supersonic flow field.
Keywords: Scramjet Combustor Design, Vortex Generators, Micro-Ramp, Flow Separation, Drag.
Scope of the Article: Machine Design