Numerical investigation on cavity structure of solid-fuel scramjet combustor |
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| Institution: | 1. Department of Mechanical Engineering, R.V. College of Engineering, Bengaluru, Karnataka, India;2. Department of Mechanical Engineering, National Institute of Technology Silchar, Assam, India;3. Department of Mechanical Engineering, Ellenki College of Engineering and Technology, Hyderabad, Telangana, India;1. School of Mechanical Engineering, Nanjing University of Science and Technology, Nanjing, 210094, PR China;2. Mechanical Engineering Department, Omdurman Islamic University, Omdurman, Sudan;1. School of Mechanical Engineering, Nanjing University of Science and Technology, Nanjing, 210094, PR China;2. Mechanical Engineering Department, Omdurman Islamic University, Omdurman, Sudan |
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| Abstract: | The influences of miscellaneous combustor structures for solid fuel scramjet combustion on the performance are investigated, including a detailed interaction analysis between shocks/waves and combustion. Hydroxyl-terminated polybutadiene is chosen as the solid fuel with the non-premixed equilibrium probability density function combustion model. The results show combustion enhancement when structure of combustor is modified. The radical emphasis is to examine the sensitivity of the properties due to variations on the length-to-depth ratio of cavity, aft wall angle, and offset ratio. It is noted that there is an appropriate structure of cavity (L/D=4, θ=45°, and Dd/Du=1.25–1.5) regarding the combustion efficiency, total pressure loss and specific impulse. The observation of function for combustor components provides instructional insight into the design considerations for a combustor of a solid-fuel scramjet. |
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| Keywords: | Solid fuel scramjet Cavity structure Shock waves Supersonic combustion |
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