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Advances in Aircraft and Spacecraft Science Volume 7, Number 3, May 2020 , pages 187-202 DOI: https://doi.org/10.12989/aas.2020.7.3.187 |
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Numerical investigation of detonation combustion wave propagation in pulse detonation combustor with nozzle |
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Pinku Debnath and K. M. Pandey
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| Abstract | ||
| The exhaust nozzle serves back pressure of Pulse detonation combustor, so combustion chamber gets sufficient pressure for propulsion. In this context recent researches are focused on influence of nozzle effect on single cycle detonation wave propagation and propulsion performance of PDE. The effects of various nozzles like convergent-divergent nozzle, convergent nozzle, divergent nozzle and without nozzle at exit section of detonation tubes were computationally investigated to seek the desired propulsion performance. Further the effect of divergent nozzle length and half angle on detonation wave structure was analyzed. The simulations have been done using Ansys 14 Fluent platform. The LES turbulence model was used to simulate the combustion wave reacting flows in combustor with standard wall function. From these numerical simulations among four acquaint nozzles the highest thrust augmentation could be attained in divergent nozzle geometry and detonation wave propagation velocity eventually reaches to 1830 m/s, which is near about C-J velocity. Smaller the divergent nozzle half angle has a significant effect on faster detonation wave propagation. | ||
| Key Words | ||
| detonation wave; nozzle shape; pulse detonation combustor; computational fluid dynamics | ||
| Address | ||
| Pinku Debnath: Department of Mechanical Engineering, National Institute of Technology Agartala, 799046, Tripura, India K. M. Pandey: Department of Mechanical Engineering, National Institute of Technology, Silchar, Assam,788010 India | ||
