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.
Highlights Some methods for characterizing mixing and heat release were established. Influence of lobe geometry on mixing and heat release of combustor was conducted. Engine performance improves with the decrease of lobe sweep angle. The optimum value point of lobe height within 0–24 mm is approximately 14 mm.
Influence of lobe geometry on mixing and heat release characteristics of solid fuel rocket scramjet combustor
Acta Astronautica ; 164 ; 212-229
2019-08-03
18 pages
Article (Journal)
Electronic Resource
English
Experimental and Numerical Investigation of a Solid-Fuel Rocket Scramjet Combustor
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