Abstract
The highly efficient and organized combustion of combustors should be achieved to improve the performance of solid fuel rocket scramjets. This study investigated the influence of changes in lobe sweep angle and height on the mixing and heat release characteristics of a solid fuel scramjet combustor on the basis of a staggered support plate structure introduced in a previous experimental study. The goal was to determine the optimal parameters of lobe sweep angle and height for subsequent engine design. Numerical simulation was conducted to quantitatively analyze the mixing and heat release characteristics of the combustor at different lobe sweep angles and heights in terms of combustion efficiency, gas mixing degree, and oxygen–fuel ratio. Results demonstrate that 1) the lobe sweep angle should be based on the width and straight section length of the staggered support plate structure. Engine performance improves with the decrease of the lobe sweep angle. 2) There is an optimum lobe height in the range of 0–24 mm, and the optimum value point is approximately 14 mm according to the proposed engine configuration.
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a callDisclaimer: All third-party content on this website/platform is and will remain the property of their respective owners and is provided on "as is" basis without any warranties, express or implied. Use of third-party content does not indicate any affiliation, sponsorship with or endorsement by them. Any references to third-party content is to identify the corresponding services and shall be considered fair use under The CopyrightLaw.
