Numerical Studies on Thrust Augmentation in High Area Ratio Rocket Nozzles by Secondary Injection

Single stage to orbit propulsion devices are being developed as part of low cost access to space endeavors. Sea level operation of high area ratio rocket nozzle used in rocket engines leads to an overexpanded flow condition resulting in high side loads. Secondary injection of propellants in high are...

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Bibliographic Details
Published in:	Journal of Applied Fluid Mechanics Vol. 10; no. 6; pp. 1605 - 1614
Main Authors:	Shyji, S., Deepu, M., Kumar, N. A., Jayachandran, T.
Format:	Journal Article
Language:	English
Published:	Isfahan Isfahan University of Technology 01-11-2017
Subjects:	Algorithms Chemical speciation Compressibility Computational fluid dynamics Conservation equations Flow simulation Injection Mathematical models Nozzle flow Nozzles Propellants Reacting flow Rescaling Rocket engines Rocket nozzles Rocket nozzles; Thrust augmentation; Turbulent reacting flows; AUSM+-up scheme; Finite volume method Scaling Sea level Secondary injection Single stage to orbit vehicles Solvers Stiffness Supersonic combustion Thrust Thrust augmentation Turbulent flow Wall pressure
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Summary:	Single stage to orbit propulsion devices are being developed as part of low cost access to space endeavors. Sea level operation of high area ratio rocket nozzle used in rocket engines leads to an overexpanded flow condition resulting in high side loads. Secondary injection of propellants in high area ratio nozzle is an attractive option to overcome the inefficiency of operation of such nozzles in sea level conditions in addition to the augmentation of thrust. A numerical study on thrust augmentation in high area ratio nozzle by secondary injection of propellants is presented here. The turbulent compressible reacting flow in rocket nozzle with auxiliary injection is simulated using conservation equations for chemical species based on finite rate chemistry model and compressible Navier-Stokes equations with AUSM+-up upwind scheme based unstuctured finite volume solver. An optimized eight step, six species reduced H2-O2finite chemistry reaction model is used to model the supersonic combustion. The indigenously developed solver has an efficient rescaling algorithm to alleviate the effect of stiffness in conventional explicit algorithm for simultaneous solution of reacting flow. The code is validated using the wall pressure and hydrogen concentration values reported for the similar high area ratio rocket nozzle. Accurate prediction of nozzle performance is possible with present turbulent reacting flow simulation as it take care of all losses in nozzle flow. Extensive computations have been performed for the performance estimation of high area ratio rocket nozzle for various prospective auxiliary injection options.
ISSN:	1735-3572 1735-3645
DOI:	10.29252/jafm.73.245.27309