Numerical Investigation of Predetonator of Pulse Detonation Engine Tube
Navneet Kumar1, Linsu Sebastian2
1Navneet Kumar, Department of Aerospace Engineering, Indian Institute of Technology, Kanpur (Uttar Pradesh), India.
2Linsu Sebastian, Department of Aerospace Engineering, University of Petroleum and Energy Studies, Dehradun (Uttarakhand), India.
Manuscript received on 10 October 2017 | Revised Manuscript received on 18 October 2017 | Manuscript Published on 30 October 2017 | PP: 52-59 | Volume-7 Issue-1, October 2017 | Retrieval Number: A5182107117/17©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: Pulse detonation engine (PDE) is future propulsion technology that involves detonation of fuel to produce thrust more efficiently than the available current engines. The PDE can provide static thrust for a ramjet or scramjet engine, or operate in combination with turbofan systems. The objective of present study was to observe the effect of predetonator (having disturbances in the form of Shchelkin spiral) on the detonation velocity, pressure and length of PDE tube. In this project a new design has been developed for Predetonator. Initiation and propagation of detonation waves inside predetonation tube has been done by two-step detonation initiation method, low energy ignition system (total energy of 50mJ), and effective Shchelkin spiral of blockage area ratio of 0.43. Liquid kerosene, gaseous oxygen and nitrogen were used as fuel, oxidizer and purge gas respectively with 420mm predetonator, a convergent-divergent nozzle and a 415mm long tube for main detonation has been used. In the present study the filling processes is modeled numerically using CFD code FLUENT. Calculations for the gas flow are carried out by solving the Navier-Stokes equations coupled with the k “turbulence model. Numerical analysis of the geometry made has been done by using GAMBIT and FLUENT for two dimensional predetonator model and results have been observed in the form of pressure, velocity and temperature contours at different time step. Numerical analysis obtained results have been compared with the calculated results from NASA CEA code for respective conditions.
Keywords: Detonation, Deflagration, Predetonator and Pulse Detonation Engines (PDE).
Scope of the Article: Machine Learning