Commenced in January 2007
Paper Count: 30750
Wall Heat Flux Mapping in Liquid Rocket Combustion Chamber with Different Jet Impingement Angles
Abstract:The influence of injector attitude on wall heat flux plays an important role in predicting the start-up transient and also determining the combustion chamber wall durability of liquid rockets. In this paper comprehensive numerical studies have been carried out on an idealized liquid rocket combustion chamber to examine the transient wall heat flux during its start-up transient at different injector attitude. Numerical simulations have been carried out with the help of a validated 2d axisymmetric, double precision, pressure-based, transient, species transport, SST k-omega model with laminar finite rate model for governing turbulent-chemistry interaction for four cases with different jet intersection angles, viz., 0o, 30o, 45o, and 60o. We concluded that the jets intersection angle is having a bearing on the time and location of the maximum wall-heat flux zone of the liquid rocket combustion chamber during the start-up transient. We also concluded that the wall heat flux mapping in liquid rocket combustion chamber during the start-up transient is a meaningful objective for the chamber wall material selection and the lucrative design optimization of the combustion chamber for improving the payload capability of the rocket.
Digital Object Identifier (DOI): doi.org/10.5281/zenodo.1339692Procedia APA BibTeX Chicago EndNote Harvard JSON MLA RIS XML ISO 690 PDF Downloads 1042
 Victor P.Zhukov, Dmitry I.Suslov, “Measurements and modelling of wall heat fluxes in rocket combustion chamber with porous injector head,” Aerospace Science and Technology 48 (2016) 67–74.
 J. Lux, D. Suslov, O.J. Haidn, On porous liquid propellant rocket engine injectors, Aerosp. Sci. Technol. 12 (2007) 469–477.
 Guiliano R, luigi Cutrone, Daniele Cardillio, “Numerical Investigation of Rocket Engine Combustion Flow Fields”, AIAA-2016-2146.
 A. Benarous, D. Karmed, R. Haoui, and A. Liazid “An Attempt to Predict The Performance Of A Rocket Combustion Chamber”, World Academy of Science, Engineering and Technology International Journal of Mechanical, Aerospace, Industrial, Mechatronic and Manufacturing Engineering Vol: 6, No: 11, 2012.
 A. Murrone, N. Fdida, C. Le Touze, L. Vingert, “Atomization of Cryogenic Rocket Engines Coaxial Injectors. Modeling Aspects and the Experimental Investigations”, Space propulsion 2014, May 2014, Cologne, Germany.
 Hagen Müller, Christoph A. Niedermeier, Jan Matheis, Michael Pfitzner and Stefan Hickel, “Large-eddy simulation of nitrogen injection at trans and supercritical conditions,” Physics of Fluids 28, 015102 (2016).
 Juan Li, Zhenwei Zhao, Andrei Kazakov, and Frederick L. Dryer, “An Updated Comprehensive Kinetic Model of Hydrogen Combustion”, International Journal of Chemical Kinetics (Vol. 36, p. 566-575 (2004)
 Mani Pourouchottamane, Francis Dupoirieux*, Lucien Vingert, Mohammed Habiballah, and Victor Burnleyt, “Numerical Analysis of the 10 Bar Mascotte Flow Field”, ONERA - B.P. 72 - 92322 Chatillon Cedex – France WAir Force Research Laboratory.
 A. Coclite, L. Cutrone, P. De Palma, G. Pascazio “Numerical investigation of high-pressure combustion in rocket engines using Flamelet/Progress-variable models” AIAA, 2 December 2014.
 Richard Farmer, Gary Cheng, Yen-Sen Chen, “CFD Simulation of Liquid Rocket Engine Injectors Part 2. Simulations of the RCM-2 Experiment”, Atomization, Combustion and Heat Transfer held in Lampoldshausen, Germany on 25-27 Mar 2001.
 A. Depoutre, S. Zurbach, D. Saucereau, J.P. Dumont, E Bodele, I. Gokalp, “Numerical calculation of MASCOTTE 60 bar case with THESEE”, Atomization, Combustion and Heat Transfer held in Lampoldshausen, Germany on 25-27 Mar 2001.
 Daniele Cardillo, Daniele Ricci, Pietro Roncioni, Francesco Battista, “Numerical Simulation of a LO2-CH4 Rocket Engine Demonstrator”, 65th International Astronautical Congress, Toronto, Canada, Sept. 2014.
 George P. Sutton & Oscar Biblarz (2001). Rocket Propulsion Elements (7th ed.). Wiley Interscience. ISBN 0-471-32642-9.
 Dexter K Huzel and David H. Huang (1971), NASA SP-125, Design of Liquid Propellant Rocket Engines.