TECHNICAL MECHANICS
ISSN (Print): 1561-9184, ISSN (Online): 2616-6380

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UDC 539.3

Technical mechanics, 2021, 1, 16 - 28

Evaluation of the high-frequency oscillation parameters of a liquid-propellant rocket engine with an annular combustion chamber

DOI: https://doi.org/10.15407/itm2021.01.016

Nikolayev O. D., Bashliy I. D., Khoriak N. V., Dolgopolov S. I.

Nikolayev O. D.
Institute of Technical Mechanics of the National Academy of Sciences of Ukraine and the State Space Agency of Ukraine

Bashliy I. D.
Institute of Technical Mechanics of the National Academy of Sciences of Ukraine and the State Space Agency of Ukraine

Khoriak N. V.
Institute of Technical Mechanics of the National Academy of Sciences of Ukraine and the State Space Agency of Ukraine

Dolgopolov S. I.
Institute of Technical Mechanics of the National Academy of Sciences of Ukraine and the State Space Agency of Ukraine

      The high-frequency instability (HF instability) of a liquid-propellant rocket engine (LPRE) during static firing tests is often accompanied by a significant increase in dynamic loads on the combustion chamber structure, often leading to the chamber destruction. This dynamic phenomenon can also be extremely dangerous for the dynamic strength of a liquid-propellant rocket engine with an annular combustion chamber. Computation of the parameters of acoustic combustion product oscillations is important in the design and static firing tests of such rocket engines. The main aim of this paper is to develop a numerical approach to determining the parameters of acoustic oscillations of combustion products in annular combustion chambers of liquid-propellant rocket engines taking into account the features of the configuration of the combustion space and the variability of the physical properties of the gaseous medium depending on the axial length of the chamber. A numerical approach is proposed. The approach is based on mathematical modeling of natural oscillations of a “shell structure of an annular chamber – gas” coupled dynamic system by using the finite element method.
      Based on the developed finite-element model of coupled spatial vibrations of the structure of the annular combustion chamber and the combustion product oscillations, the oscillation parameters of the system under consideration (frequencies, modes, and effective masses) for its dominant acoustic modes, the vibration amplitudes of the combustion chamber casing, and the amplitudes of its vibration accelerations can be determined. The operating parameters of the liquid-propellant rocket engine potentially dangerous for the development of thermoacoustic instability of the working process in the annular combustion chamber can be identified. For the numerical computation of the dynamic gains (in pressure) of the combustion chamber, a source of harmonic pressure excitation is introduced to the finite element model of the dynamic system “shell structure of an annular configuration – gas” (to the elements at the start of the chamber fire space).
      The developed approach testing and further analysis of the results were carried out for an engine with an annular combustion chamber (with a ratio of the outer and inner diameters of 1.5) using liquid oxygen – methane as a propellant pair.
      The system shapes and frequencies of longitudinal, tangential and radial modes are determined. It is shown that the frequency of the first acoustic mode in the case of a relatively low stiffness of the combustion chamber casing walls can be reduced by 40 percent in comparison with the frequency determined for a casing with rigid walls.
     

liquid propellant rocket engine, annular combustion chamber, methane–oxygen propellant, high-frequency engine instability, oscillation frequencies

1. Hall Joshua N., Hartsfield Carl R., Simmons Joseph R., Branam Richard D. Performance & Thrust-to-Weight Optimization of the Dual Expander Aerospike Nozzle Upper Stage Rocket Engine. AIAA Report. 2012. 50260651/Q0BD. URL: https://arc.aiaa.org/doi/abs/10.2514/6.2011-419 (Last accessed on October 25, 2020).

2. Bell G., Weightman J., Knast T., Tan D., Mason-Smith N., Wong M., Jurg M. An additively manufactured CNG/GOX aerospike rocket engine: design process. 68th International Astronautical Congress. (Adelaide, Australia, 25 - 29 September, 2017) Adelaide, Australia, 2017. IAC-17-C4.1.12. URL: https://iafastro.directory/iac/paper/id/39522/summary/ (Last accessed on October 25, 2020).

3. Bacha C., Schongarth S., Bust B., Propst M., Sieder-Katzmann J., Tajmar M. How to steer an aerospike. 69th International Astronautical Congress. (Bremen, October, 2018). Bremen, 2018. IAC-18-C4.3.15 URL: https://www.researchgate.net/publication/328145907_How_to_steer_ an_aerospike (Last accessed on October 25, 2020).

4. Natanzon M. S. Combustion Instability. Moscow: Mashinostroyeniye, 1986. (in Russian).

5. Dranovsky M. L. Combustion Instabilities in Liquid Rocket Engines: Testing and Development Practices in Russia. AIAA. Progress in Astronautics and Aeronautics. 2007. V. 221. 321 pp. https://doi.org/10.2514/4.866906

6. Il'chenko M. A., Kryutchenko V. V., Mnatsakyan Yu. S. Stability of the Working Process in Flying Vehicle Engines. Moscow: Mashinostroyeniye, 1995. (in Russian).

7. Klein S., Borner M., Hardi J. S., Suslov D., Oschwald M. Injector coupled thermoacoustic instabilities in an experimental LOX methane rocket combustor during start up. CEAS Space Journal. 2020. Pp. 267-279. URL: https://www.ist.rwth-aachen.de/go/id/raks/file/794257/lidx/1/ (Last accessed on October 25, 2020). https://doi.org/10.1007/s12567-019-00294-4

8. Liquid propellant rocket. Ñombustion instability. National Aeronautics and Space Administration. Washington, 1972. 637 pp. SP-194. URL:https://ntrs.nasa.gov (Last accessed on October 25, 2020).

9. Kaess R., Koeglmeier S., Sattelmayer T., Schulze M., Oschwald M., Hardi J. HF combustion stability. Research activities in Germany. Space Propulsion Conference. Rome, 2016. 12 pp. SP2016_3124816. URL: https://elib.dlr.de/107846/1/Kaess2016_SP2016_3124816.pdf (Last accessed on October 25, 2020).

10. Kohnke P. Ansys Inc. Theory Manual. 001369. Twelfth Edition. Canonsburg: SAS IP, 2001, 1266 pp.

11. Zienkiewicz O. C. The Finite Element Method in Engineering Science. Moscow: Mir, 1975. 541 pp. (in Russian).

12. Lependin L. F. Acoustics. Moscow: Vysshaya Shkola, 1978. 448 pp. (in Russian).

13. Roache P. Computational Fluid Dynamics. Moscow: Mir, 1980. 618 pp. (in Russian).

14. Bathe K. J. Finite Element Procedures. Prentice-Hall: Englewood Cliffs, 1996.

15. Zienkiewicz O. C., Newton R. E. Coupled vibrations of a structure submerged in a compressible fluid. Proceedings of the Symposium on Finite Element Techniques. University of Stuttgart. Germany. June 1969. URL: https://repository.tudelft.nl/islandora/object/uuid%3A27785b4f-3709-4fa9-a189-6ce1d3365564 (Last accessed on October 25, 2020).

16. Oschwald M., Farago Z., Searby G., Cheuret F. Resonance frequencies and damping of a combustor acoustically coupled to an absorber. Journal of Propulsion and Power. 2008. V. 24. No. 3. Pp. 524-533. URL: https://www.researchgate.net/publication/225000485_Resonance_Frequencies_and_Damping_of_a_ Cylindrical_Combustor_Acoustically_Coupled_to_an_Absorber (Last accessed on October 25, 2020). https://doi.org/10.2514/1.32313

17. Crocco L. Cheng S.I. Theory of Combustion Instability in Liquid Propellant Rocket Motors. . London: Butterworths Scientific Publications, New York: Interscience Publishers Inc., 1956. 200 pp. URL: https://ui.adsabs.harvard.edu/abs/1957JFM.....2..100H/abstract (Last accessed on October 25, 2020). https://doi.org/10.1017/S0022112057210774

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