×

zbMATH — the first resource for mathematics

Application of a partitioned field approach to transient aerothermal problems in rocket nozzles. (English) Zbl 1391.76266
Summary: The structural body of a rocket nozzle is dynamically exposed to high thermal and mechanical loads, which are caused by the hot gas flow. The flow field is itself significantly influenced by the shape and temperature changes of the nozzle wall. Additionally, for typical hot nozzle walls thermal radiation cannot be neglected. To ensure reliable results the unsteady aerothermoelastic interaction and the radiation have to be taken into account in computational investigations. A coupling method is proposed which is able to transfer unsteady mechanical and thermal loads from a fluid solver to a structural solver and transfer deformations and surface temperatures back. Especially in early design steps a fast but reliable simulation approach is necessary. Therefore, a solver using reduced structural models is applied. To be able to consider the radiation within the aerothermoelastic simulation, the structural solver is extended by appropriate computational methods. Also the ability to consider temperature dependent material behaviour is implemented. The presented computational results show the capability of the current fluid-structure interaction method to simulate the aerothermal behaviour of a dual bell nozzle. The computational predictions of the structural solver of the temperature field considering external and internal radiation and also considering temperature-dependent material properties are validated against computational results from a commercial FE solver and experiments.
MSC:
76G25 General aerodynamics and subsonic flows
76N15 Gas dynamics, general
Software:
ABAQUS; TAU
PDF BibTeX XML Cite
Full Text: DOI
References:
[1] Forster C, Cowles F. Experimental study of gas-flow separation in overexpanded exhaust nozzles for rocket motors. Progress report, 4-103, Jet Propulsion Laboratory; 1949
[2] Birken P, Quint KJ, Hartmann S, Meister Ai. On coupling schemes for heat transfer in FSI applications. In: Proceedings inter-workshop on fluid-structure interaction: theory, numerics and applications. Herrsching, Germany; 2009
[3] Felippa, C. A.; Park, K. C.; Farhat, C., Partitioned analysis of coupled mechanical systems, Comput Meth Appl Mech Eng, 190, 24, 3247-3270, (2001) · Zbl 0985.76075
[4] Farhat, C.; Lesoinne, M.; Le Tallec, P., Load and motion transfer algorithms for fluid/structure interaction problems with non-matching discrete interfaces: momentum and energy conservation, optimal discretization and application to aeroelasticity, Comput Meth Appl Mech Eng, 157, 1, 95-114, (1998) · Zbl 0951.74015
[5] Jaiman, R. K.; Jiao, X.; Geubelle, P. H.; Loth, E., Conservative load transfer along curved fluid-solid interface with non-matching meshes, J Comput Phys, 218, 1, 372-397, (2006) · Zbl 1158.76405
[6] Förster, C.; Wall, W. A.; Ramm, E., Artificial added mass instabilities in sequential staggered coupling of nonlinear structures and incompressible viscous flows, Comput Meth Appl Mech Eng, 196, 7, 1278-1293, (2007) · Zbl 1173.74418
[7] Roe, B.; Jaiman, R.; Haselbacher, A.; Geubelle, P. H., Combined interface boundary condition method for coupled thermal simulations, Int J Numer Meth Fluids, 57, 3, 329-354, (2008) · Zbl 1241.80009
[8] Jaiman, R.; Geubelle, P.; Loth, E.; Jiao, X., Transient fluid-structure interaction with non-matching spatial and temporal discretizations, Comput Fluids, 50, 1, 120-135, (2011) · Zbl 1271.76242
[9] Garelli, L.; Paz, R. R.; Storti, M. A., Fluid-structure interaction study of the start-up of a rocket engine nozzle, Comput Fluids, 39, 7, 1208-1218, (2010) · Zbl 1242.76098
[10] Lüdeke H, Calvo JB, Filimon A. Fluid structure interaction at the ariane-5 nozzle section by advanced turbulence models. In: ECCOMAS CFD, TU Delft, The Netherlands; 2006
[11] Parsons ID, Alavilli P, Namazifard A, Acharya A, Jiao X, Fiedler R. Coupled simulations of solid rocket motors. AIAA paper, 3456; 2000.
[12] Liu, Q.; Luke, E. A.; Cinnella, P., Coupling heat transfer and fluid flow solvers for multidisciplinary simulations, J Thermophys Heat Transfer, 19, 4, 417-427, (2005)
[13] Meinel M, Einarsson GO. The FlowSimulator framework for massively parallel CFD applications. In: Para 2010 - state of the art in scientific and parallel computing; 2002.
[14] Gerhold, T., Overview of the hybrid RANS code TAU, (Notes on numerical fluid mechanics and multidisciplinary design, vol. 89, (2005), Springer-Verlag), 81-92 · Zbl 1273.76313
[15] Rittweger A. Statik, Stabilität und eigenschwingungen anisotroper rotationsschalen beliebigen meridians mit der Übertragungsmatrizen-methode. Doctoral thesis. RWTH Aachen University; 1992
[16] Rittweger, A.; Scherman, T.; Reimerdes, H.-G.; Öry, H., Influence of geometric imperfections on the load capacity of orthotropic stiffened and composite shells of revolution with arbitrary meridians and boundary conditions, Thin-Wall Struct, 23, 237-254, (1995)
[17] Öry, H.; Reimerdes, H. G.; Schmid, T.; Rittweger, A.; Gomez-Garcia, J., Imperfection sensitivity of an orthotropic spherical shell under external pressure, Int J Non-Linear Mech, 37, 669-689, (2002) · Zbl 1346.74122
[18] Takezono, S.; Tao, K.; Aoki, T.; Inamura, E., Elasto/visco-plastic deformation of shells of revolution under thermal loading due to fluid, JSME Int J, 38, 185-193, (1995)
[19] Nunes, E.; Naraghi, M., Numerical model for raditive heat transfer analysis in arbitrary shaped axisymmetric enclosures with gaseous media, Numer Heat Trans Part A: Appl, 33, 495-513, (2007)
[20] Beckert, A., Coupling fluid (CFD) and structural (FE) models using finite interpolation elements, Aerosp Sci Technol, 4, 13-22, (2000) · Zbl 0999.74106
[21] Boucke A. Kopplungswerkzeuge für aeroelastische Simulationen. Doctoral thesis. RWTH Aachen University; 2003
[22] Braun C. Ein modulares Verfahren für die numerische aeroelastische analyse von luftfahrzeugen. Doctoral thesis. RWTH Aachen University; 2007
[23] Reimer, L.; Braun, C.; Wellmer, G.; Behr, M.; Ballmann, J., Development of a modular method for computational aero-structural analysis of aircraft, (Schröder, W., Summary of flow modulation and fluid-structure interaction findings—results of the collaborative research center SFB 401 at the RWTH Aachen University, (2008), Springer-Verlag Aachen, Germany)
[24] Heath, M. T., Scientific computing: an introductory survey, (2002), McGraw-Hill New York (United States) · Zbl 0903.68072
[25] Beckert, A.; Wendland, H., Multivariate interpolation for fluid-structure interaction problems using radial basis functions, Aerosp Sci Technol, 5, 125-134, (2001) · Zbl 1034.74018
[26] Quaranta G, Masarati P, Mantegazza P. A conservative mesh-free approach for fluid-structure interface problems. In: Proceedings int conf comp methods coupled probl sci eng Barcelona. Spain; 2005 · Zbl 1236.70006
[27] Hosters N, Klaus M, Schieffer G, Behr M, Reimerdes H-G. Towards aerothermoelastic simulations of supersonic flow through nozzles. In: Proceedings 4th European conference for aerospace sciences EUCASS. St. Petersburg, Russia; 2011
[28] Wendland, H., Piecewise polynomial, positive definite and compactly supported radial functions of minimal degree, Adv Comput Math, 4, 389-396, (1995) · Zbl 0838.41014
[29] Kalnins, A., Analysis of shells of revolution subjetcted to symmetrical and non-symmetrical loads, J Appl Mech, 31, 467, (1964)
[30] Walker, D. W.; Dongarra, J. J., MPI: a standard message passing interface, Supercomputer, 12, 56-86, (1996)
[31] Genin C, Gernoth A, Stark C. Experimental and numerical study of heat flux in dual bell nozzles. In: 47th AIAA joint propulsion conference. San Diego, CA. USA; 2011
[32] Spalart P, Allmaras S. A one-equation turbulence model for aerodynamic flows. Technical report AIAA-92-0439, American Institute of Aeronautics and Astronautics; 1992
This reference list is based on information provided by the publisher or from digital mathematics libraries. Its items are heuristically matched to zbMATH identifiers and may contain data conversion errors. It attempts to reflect the references listed in the original paper as accurately as possible without claiming the completeness or perfect precision of the matching.