Equivalence ratio and constriction effects on RBCC thrust augmentation |
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| Authors: | M Koupriyanov J Etele |
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| Institution: | 1. Department of Chemistry, Box 351700, University of Washington, Seattle, WA 98195, USA;2. Air Force Research Laboratory/RQRC, 10 E Saturn Boulevard, Edwards AFB, CA 93524, USA;3. Pacific Northwest National Laboratory, PO Box 999, MS P7-50, Richland, WA 99352, USA;4. Applied Chemicals and Materials Division, National Institute of Standards and Technology, Boulder, CO 80305, USA;1. Science and Technology on Combustion, Internal Flow and Thermal-structure Laboratory, Northwestern Polytechnical University, Xi’an, Shaanxi 710072, PR China;2. Beijing Aerospace Technology Institute, Beijing 100074, PR China;1. Institute of Space Planes and Hypersonic Technologies, School of Astronautics, Northwestern Polytechnical University, Xi''an, 710012, China;2. Graduate School of Hubei Aerospace Technology Academe, Wuhan, 430048, China |
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| Abstract: | A theoretical analysis of a variable area rocket based combined cycle engine with and without simultaneous mixing and combustion is presented. The flowfield is solved using a steady, quasi-one-dimensional, inviscid control volume formulation with combustion effects included via a generalized equilibrium calculation. Compression augmentation is shown to be sensitive to the equivalence ratio within the primary rocket chamber, where ejector section performance is greatest at both low and high equivalence ratios but near a minimum at stoichiometric conditions. The thrust generated by the RBCC engine compared to that generated by the same rocket in isolation can be increased by as much as 12% at constriction ratios of between 45% and 50%. Thrust augmentation is also shown to vary with equivalence ratio, where for a fixed geometry the maximum thrust is generated at equivalence ratios slightly below unity. |
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