| Biography | |
|---|---|
 Prof. K. M. Pandey National Institute of Technology Silchar, India |
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| Title: Impact of wall fuel injector location in scramjet combustor on combustion performance | |
| Abstract: High speed vehicles are getting popularity at the Global level. Since the conventional aerospace vehicle has few restriction, among them weight of the aircraft is major concern however to reach up to supersonic speed, aircraft engine has to be designed in such a way that the internal geometry can sustain their higher temperature and pressure loads. To uncover the major problems, distinguished scientist and researchers have contributed to explore various corner of the flaws of supersonic combustion ramjet engine (Scramjet). Scramjet engine does not involve any moving or rotating parts alike other jet engines, hence the thrust to weight ratio is superior. Apart from this, engine does not carry any additional tank for the oxidizer because atmospheric air is utilised. Hence the selection of appropriate combustor geometry is necessary to obtain desirable performance. The present article has selected DLR scramjet model, which was first performed in on German Aerospace Centre (DLR). The selected experimental model utilises parallel fuel injection system by means of wedge shaped strut placed at the middle of the combustor. Initially the validation has been done by comparing both reacting and non-reacting type of cases nonetheless percentage of uncertainty has also been under acceptable limit. To understand the impact of wall fuel injector in the selected scramjet combustor model, different sets of numerical investigation has been performed. All the numerical observation is done by using Ansys 14.0 fluent solver. Since the validation of this model shows good agreement to the numerical outcome, hence the similar steps have also been followed to compute the further examination. The computational outcome suggests that the plot of combustion efficiency follows the two sectional steps i.e. rapid chemical reaction near in the longitudinal direction and the gradual fuel consumption is identified in second section. The outcome shows that the abrupt change is seen in 68 mm transverse fuel injector model, which shows 96 % combustion efficiency. Keywords: DLR Scramjet model; Wedge shaped strut; Multi Fuel injection system; Reacting flow; Hydrogen. | |
| Biography: Dr. Pandey did his PhD in Mechanical Engineering in 1994 from IIT Kanpur. He has published and presented more than 325 papers in International & National Journals and Conferences. His h-index in google scholar is 26.. Currently he is working as Senior Professor in Department of Mechanical. Engineering ,of National Institute of Technology, Silchar, Assam, India.. Dr. Pandey has got more than 70 SCI indexed journal papers and more than 180 research articles are indexed in Scopus. His h-index in Scopus is 19. He has delivered many key note speeches in India, Singapore, and China. In the year 2020. Dr Pandey has given 3 keynote speeches for conferences held in Beijing ICMEM 2020,in ICNFM held in Shanghai on 22 December 2020 and Keynote aSpeaker in 5GAI INSAI Connected Global Forum & 2nd International Conference on Artificial Intelligence and Advanced Manufacturing (AIAM2020) held on 26 December 2020 in Shanghai, P.R.China. In many earlier occasions also he had given speech in Singapore in 2018 and in Guangzhou in GMEE 2019 in December.In few conferences he has served as co-editor and general chair also. | |
