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Инновационная методика расчета и проектирования камеры сгорания…
Инженерный журнал: наука и инновации
# 12·2016 11
Innovative methodology for calculation and design
of liquid-propellant rocket engine combustion chamber
© O.V. Korotkaya
Bauman Moscow State Technical University, Moscow, 105005, Russia
The methodology for mathematical modeling which makes it possible to perform calcula-
tions and design of liquid-propellant rocket engine combustion chambers, minimizing the
number of bench tests, has been proposed in this article. Nowadays the numerous fire
tests are the basic methods to test the strength of the combustion chambers. By combining
a number of software packages (ANSYS, pSeven) the developed methodology enables us
not only to perform a checking calculation but to design an optimal structure as well. We
describe a step-by-step sequence of actions. Moreover, we give some recommendations
for a calculation of a LPRE combustion chamber on several operating modes in terms of
low-cycle fatigue. The proposed methodology has been approved while designing the
11D58MF cruise engine.
Keywords:
mathematical modeling, finite-element method, substructure, cyclic symmetry,
anisotropy coefficients, optimization, mode of deformation, nozzle, combustion chamber,
liquid-propellant rocket engine, cooling channels.
REFERENCES
Feodosyev V.I.
Prochnost kamery zhidkostnogo raketnogo dvigatelya
[The
strength of the liquid-propellant rocket engine combustion chamber]. Moscow,
Oborongiz Publ., 1957, 212 p.
Korotkaya O.V., Gavryushin S.S.
Izvestiya vysshikh uchebnykh zavedeniy. Mash-
inostroenie — Proceedings of Higher Educational Institutions. Machine Build-
ing
, 2016, no. 1 (670), pp. 78–86. DOI: 10.18698/0536-1044-2016-1-78-86
Kuhl D., Riccius J., Haidn O.J. Thermomechanical Analysis and Optimization
of Cryogenic Liquid Rocket Engines.
Journal of Propulsion and Power
, July–
August 2002, vol. 18, no. 4, pp. 835–846.
Sutton G.P., Biblarz O.
Rocket Propulsion Elements
. New York, John Wiley &
Sons, 2001, 751 p.
Naraghi M.H.N.
A Computer Code for Three-Dimensional Rocket Thermal
Evaluation
.New York, Tara Technologies, 2002, 106 p.
Naraghi M.H., Dunn S., Coats D. A Model for Design and Analysis of Regen-
eratively Cooled Rocket Engines.
AIAA-2004-3852, Joint Propulsion Confer-
ence, Fort Lauderdale
, 2004, 13 p.
Asraff A.K., Sunil S., Muthukumar R., Ramanathan T.J. Stress analysis & life
prediction of a cryogenic rocket engine thrust chamber considering low cycle
fatigue, creep and thermal ratchetting.
Transactions of the Indian Institute of
Metals
, April–June 2010, vol. 63, no. 2–3, pp. 601–606.
Babu A., Asraff A.K., Philip N. Fatigue life prediction of a rocket combustion
chamber.
IOSR Journal of Mechanical and Civil Engineering (IOSR-JMCE)
,
September–October 2014, vol. 11, no. 5, pp. 12–20.
Asraff A.K., Sheela S., Eapen R.K., Babu A. Cyclic stress analysis of a rocket
engine thrust chamber using chaboche constitutive model.
Transactions of the
Indian Institute of Metals
, March 2016, vol. 69, no. 2, pp. 495–500.