Skip to main content
SpringerLink
Log in

On the method for hot-fire modeling of high-frequency combustion instability in liquid rocket engines

  • Published:
KSME International Journal Aims and scope Submit manuscript

Abstract

This study presents the methodological aspects of combustion instability modeling and pro-vides the numerical results of the model (sub-scale) combustion chamber, regarding geometrical dimensions and operating conditions, which are for determining the combustion stability boundaries using the model chamber. An approach to determine the stability limits and acoustic characteristics of injectors is described intensively. Procedures for extrapolation of the model operating parameters to the actual conditions are presented, which allow the hot-fire test data to be presented by parameters of the combustion chamber pressure and mixture (oxidizer/fuel) ratio, which are customary for designers. Tests with the model chamber, based on the suggested scaling method, are far more cost-effective than with the actual (full-scale) chamber and useful for injector screening at the initial stage of the combustor development in a viewpoint of combustion instabilities.

This is a preview of subscription content, log in via an institution to check access.

Access this article

Log in via an institution

Price excludes VAT (USA)
Tax calculation will be finalised during checkout.

Instant access to the full article PDF.

Institutional subscriptions

Similar content being viewed by others

Abbreviations

Ath :

Nozzle throat area of rocket engine

C:

Sound velocity

C* :

Characteristic velocity

f:

Frequency

idem:

The same as the actual condition

Km :

O/F mixture ratio\(( = \dot m_o /\dot m_f )\)

L:

Length

M:

Mach number

\(\dot m\) :

Mass flow rate

n i :

Total number of main injectors

p:

Pressure

Q:

Volumetric flow rate

q:

Dynamic head ( = ρU2)

R:

Stability margin

U:

Injection velocity

W:

Molecular weight

α:

Excess-oxidizer coefficient

αmn :

Eigenvalue variable

П1 : Dependent stability parameter:

П2 : Governing (or independent) stability parameter

ρ : Density:

τ : Characteristic time

A:

Nominal or design operation regime of actual combustion chamber

a:

Actial (full-scale) chamber or condition

ch:

Combustion chamber

chem:

Chemical reaction

cyl:

Cylindrical part of combustion chamber

(c):

With a closed end

f:

Fuel

fm :

Auxiliary injectors for film cooling

i:

Per injector orifice

ig:

Auxiliary injectors for ignition

L:

Longitudinal mode

liq:

Liquid

m:

Model chamber or condition

mix:

Mixing

mL:

Them-th longitudinal mode

noz:

Nozzle part of combustion chamber

O2 :

Oxygen

o:

Oxidizer

(o):

With an open end

tot:

Total

References

  • Culick, F. E. C. and Yang, V., 1995, in Liquid Rocket Engine Combustion Instability (V. Yang, and W. E. Anderson, eds.). Progress in Astronautics and Aeronautics, Vol. 169, AlAA, Washington DC, pp. 3–38.

    Google Scholar 

  • Dexter, C. E., Fisher, M. F.. Hulka, J. R., Denisov, K. P.. Shibanov, A. A. and Agarkov, A. F., 1995, “Scaling Techniques in Liquid Rocket Engine Combustion Devices Testing.”The Second International Symposium on Liquid Rocket Engines, Paris.

  • Fisher, S. C, Dodd, F. E. and Jensen, R. J., 1995. inLiquid Rocket Engine Combustion Instability (V. Yang, and W. E.Anderson, eds.),Progress in Astronautics and Aeronautics, Vol. 169, AIAA, Washington DC, pp. 545–564.

    Google Scholar 

  • Harrje, D.J. and Reardon, F. H. (eds.), 1972,Liquid Propellant Rocket Combustion Instability, NASA SP-194.

  • McManus, K. R., Poinsot, T. and Candel, S. M., 1993, “A Review of Active Control of Combustion Instabilities,”Progress in Energy and Combustion Science, Vol. 19, pp. 1–29.

    Article  Google Scholar 

  • Natanzon, M. S., 1986,Combustion Instability (Translated by F. E. C. Culick in 1996), Mashinostroyeniye, Moscow.

    Google Scholar 

  • Seo, S., 2003, “Combustion Instability Mechanism of a Lean Premixed Gas Turbine Combustor,”KSME International Journal, Vol. 17, No. 6, pp.906–913.

    Article  Google Scholar 

  • Sohn, C. H., 2002, “Unsteady Analysis of Acoustic Pressure Response in N2 Diluted H2 and Air Diffusion Flames,”Combustion and Flame, Vol. 128, pp. 111–120.

    Article  Google Scholar 

  • Sohn, C. H., Seol, W. S., Lee, S. Y., Kim, Y. M. and Lee, D. S., 2003, “Application of Combustion Stabilization Devices to Liquid Rocket Engine,”Journal of The Korean Society for Aeronautical and Space Sciences, Vol.31, No. 6, pp. 79–87.

    Google Scholar 

  • Sohn, C. H., Kim, S.-K. and Kim, Y. -M, 2004, “Effects of Various Baffle Designs on Acoustic Characteristics in Combustion Chamber of Liquid Rocket Engine,”KSME International Journal, Vol. 18, No. 1, pp. 154–161.

    Article  Google Scholar 

  • Sutton, G. P., 1992,Rocket Propulsion Elements, 6th Ed., John Wiley & Sons, Inc., New York.

    Google Scholar 

  • Zucrow, M.J. and Hoffman, J. D, 1977,Gas Dynamics, Vol. II, John Wiley & Sons, Inc., New York.

    Google Scholar 

Download references

Author information

Authors and Affiliations

  1. Department of Aerospace Engineering, Chosun University, 501-759, Gwangju, Korea

    Chae Hoon Sohn

  2. Rocket Engine Department, Korea Aerospace Research Institute, P.O.Box 113, 305-600, Yusung, Daejeon, Korea

    Woo-Seok Seol

  3. Research Institute of Chemical Machine Building (NIICHIMMASH), Sergiev Posad, Russia

    Alexander A. Shibanov & Valery P. Pikalov

Authors
  1. Chae Hoon Sohn
    View author publications

    You can also search for this author in PubMed Google Scholar

  2. Woo-Seok Seol
    View author publications

    You can also search for this author in PubMed Google Scholar

  3. Alexander A. Shibanov
    View author publications

    You can also search for this author in PubMed Google Scholar

  4. Valery P. Pikalov
    View author publications

    You can also search for this author in PubMed Google Scholar

Corresponding author

Correspondence to Chae Hoon Sohn.

Rights and permissions

Reprints and permissions

About this article

Cite this article

Sohn, C.H., Seol, WS., Shibanov, A.A. et al. On the method for hot-fire modeling of high-frequency combustion instability in liquid rocket engines. KSME International Journal 18, 1010–1018 (2004). https://doi.org/10.1007/BF02990873

Download citation

  • Received:

  • Revised:

  • Published:

  • Issue Date:

  • DOI: https://doi.org/10.1007/BF02990873

Key Words

Search

Navigation