One-dimensional acoustic analysis of spray combustion in liquid propellant rocket chambers

Michael M. Micci, Mohammed Habiballah

Research output: Contribution to conferencePaperpeer-review

Abstract

The operation of an experimental subscale liquid oxygen/gaseous hydrogen rocket chamber where the How is predominantly one-dimensional offers both experimental and analytical simplifications. By making unsteady pressure and velocity (by means of magnetic velocimetry) measurements at various locations within a motor wherein the flow is predominantly axial in direction, one is able to obtain the acoustic admittance as a function of axial location within the chamber. Comparing the measured pressure and velocity oscillations with a one-dimensional model of the chamber gas dynamics and droplet evaporation and combustion can shed light on which individual processes contribute to cryogenic engine combustion instability. To this end, a two-phase one-dimensional linearized model of the combustion chamber was developed. Results are shown for the steady-state variables with all chamber source terms and for the acoustic variables in the absence of fluctuating source terms.

Original languageEnglish (US)
DOIs
StatePublished - 1996
Event32nd Joint Propulsion Conference and Exhibit, 1996 - Lake Buena Vista, United States
Duration: Jul 1 1996Jul 3 1996

Other

Other32nd Joint Propulsion Conference and Exhibit, 1996
CountryUnited States
CityLake Buena Vista
Period7/1/967/3/96

All Science Journal Classification (ASJC) codes

  • Energy Engineering and Power Technology
  • Electrical and Electronic Engineering
  • Mechanical Engineering
  • Control and Systems Engineering
  • Aerospace Engineering

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