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Flame response to acoustic excitation in a rectangular rocket combustor with LOx/H2 propellants

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Abstract

Research efforts are currently underway at the German Aerospace Center (DLR) Lampoldshausen, which aim to understand the mechanisms by which self-sustaining oscillations in combustion chamber pressure, known as high frequency combustion instabilities, are driven. Testing has been conducted in the rectangular combustor ‘BKH’, running cryogenic oxygen and hydrogen propellants under pressure and injection conditions which are representative of real rocket engines and with acoustic forcing. For the first time, such tests with LOx/H2 propellants and acoustic forcing have been conducted at combustion chamber pressures above 10 bar, the reported results herein from a test at 42 bar. Optical access to the combustor allowed the application of high speed hydroxyl radical (OH*) chemiluminescence imaging of the flame during periods of forced excitation of acoustic resonance modes of the combustion chamber. This paper reports the investigation of flame response to acoustic excitation. Both fluctuation in OH* emission intensity and deflection of the flame at frequencies corresponding to the excitation frequency have been observed. These responses are then discussed as potential indicators of driving mechanisms for combustion instabilities.

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Abbreviations

BKH:

Combustor H

CNRS:

Centre national de la recherche scientifique (French National Centre for Scientific Research)

DLR:

Deutsches Zentrum für Luft- und Raumfahrt (German Aerospace Center)

GOx:

Gaseous oxygen

H2 :

Hydrogen

HF:

High frequency

LOx:

Liquid oxygen

ONERA:

Office National d’Etudes et Recherches Aérospatiales (French Aerospace Lab)

c :

Acoustic velocity (speed of sound)

γ :

Ratio of specific heats

D :

Droplet diameter

μ :

Dynamic viscosity

Pcc :

Combustion chamber pressure

p :

Mean (static) pressure

p′:

Acoustic (dynamic) pressure

ρ :

Density

σ :

Surface tension

U :

Velocity

u′:

Acoustic particle velocity (displacement speed)

References

  1. Harrje, D.T., Reardon, F.H.: Liquid propellant rocket combustion instability. NASA, Washington (1972)

    Google Scholar 

  2. Yang, V., Anderson, W.: Liquid rocket engine combustion instability. AIAA, Washington (1995)

    Google Scholar 

  3. Heidmann, M.F.: Oxygen-jet behavior during combustion instability in a two-dimensional combustor. NASA TN D-2725 (1965)

  4. Tischler, A.O., Male, T.: Oscillatory combustion in rocket propulsion engines. In: Proceedings of the Gas Dynamics Symposium on Aerothermochemistry, Northwestern University, Evanston, IL, 22–24 Aug 1955

  5. Knapp, B., Oschwald, M.: High speed visualization of flame response in a LOx/H2 combustion chamber during external excitation. In: 12th International Symposium on Flow Visualization, Göttingen, Germany, 10–14 Sept 2006

  6. Rey, C., Ducruix, S., Richecoeur, F., Scouflaire, P., Vingert, L., Candel, S.: High frequency combustion instabilities associated with collective interactions in liquid propulsion. In: 40th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, Fort Lauderdale, FL, 11–14 July 2004

  7. Méry, Y., Ducruix, S., Scouflaire, P., Candel, S.: Injection coupling with high amplitude transverse modes: experimentation and simulation. In: 2nd Colloque INCA, Rouen, France, 23–24 Oct 2008

  8. Wanhainen, J.P., Parish, H.C., Conrad, E.W.: Effect of propellant injection velocity on screech in 20,000-pound hydrogen-oxygen rocket engine. NASA TN D-3373 (1966)

  9. Gordon, S., McBride, B.J.: Computer program for calculation of complex chemical equilibrium compositions and applications. Part 1: analysis. NASA-RP-1311 (1994)

  10. Mayer, W., Ivancic, B., Schik, A., Hornung, U.: Propellant atomization in LOx/GH2 rocket combustors. In: 34th AIAA/AME/SAE/ASEE Joint Propulsion Conference & Exhibit, Cleveland, OH, 13–15 July 1998

  11. Mayer, W., Tamura, H.: Propellant injection in a liquid oxygen/gaseous hydrogen rocket engine. J. Propuls. Power 12, 1137–1147 (1996)

    Article  Google Scholar 

  12. Sliphorst, M.: High frequency combustion instabilities of LOx/CH4 spray flames in rocket engine combustion chambers. Doctoral Thesis, Technische Universiteit Delft, Delft, The Netherlands (2011)

  13. Vieille, B., Chauveau, C., Gokalp, I.: Studies on the break-up regimes of LOx droplets. In: 37th AIAA Aerospace Sciences Meeting and Exhibit, Reno, Nevada, 11–14 Jan 1999

  14. Gicquel, P.P., Brisson, E.: Spray characterization in two phase reactive flows. In: 5e Congrès Francophone de Vélocimétrie Laser, Rouen, France, 24–27 Sept 1996

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Acknowledgments

The Authors are grateful to the crew of the P8 test bench as well as Dmitry Suslov and Philipp Groß for their professional efforts in test operations. Many thanks also to Walter Clauß for design and operation of optical diagnostics, and to Maike Neuland, Jannis Schücker and Harvey Camilo Gomez Martinez for their assistance in processing test data. Research undertaken for this report has been assisted with a grant from the Smith Fund (http://www.smithfund.org.au). The support is acknowledged and greatly appreciated. The Smith Fund by providing funding for this project does not verify the accuracy of any findings or any representations contained in it. Any reliance on the findings in any written report or information provided to you should be based solely on your own assessment and conclusions. The Smith Fund does not accept any responsibility or liability from any person, company or entity that may have relied on any written report or representations contained in this report if that person, company or entity suffers any loss (financial or otherwise) as a result.

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Authors and Affiliations

  1. Institute of Space Propulsion, German Aerospace Center (DLR), Lampoldshausen, 74239, Hardthausen, Germany

    Justin Hardi & Michael Oschwald

  2. School of Mechanical Engineering, The University of Adelaide, Adelaide, SA, 5005, Australia

    Justin Hardi & Bassam Dally

Authors
  1. Justin Hardi
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  2. Michael Oschwald
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  3. Bassam Dally
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Correspondence to Justin Hardi.

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Hardi, J., Oschwald, M. & Dally, B. Flame response to acoustic excitation in a rectangular rocket combustor with LOx/H2 propellants. CEAS Space J 2, 41–49 (2011). https://doi.org/10.1007/s12567-011-0020-z

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  • DOI: https://doi.org/10.1007/s12567-011-0020-z

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