Shear coaxial injector spray combustion experiments in a single element rocket chamber

A. Maskrey, C. Puissant, M. Glogowski, M. M. Micci

Research output: Contribution to conferencePaper

Abstract

A hot-fire combustion chamber designed for chamber pressures up to 10 Mpa and utilizing liquid oxygen and gaseous hydrogen has been operated with one full-size SSME preburnerelement at full scale LOX flow rates. Chamber pressures between 2 and 3 Mpa ad oxidizerto fuel mixture ratios between 2.5 and 4.0 were achieved with a LOX flow rate of 0.1113 kg/s. Results from a linearized lumped-element model of the acoustic response of the injector, combustion and LOX vaporization processes were compared to amplitudes of spontaneous chamber and fuel plenum acoustic pressure oscillations measured during chamber operation. The frequency at which the highest chamber acoustic amplitudes occurred coincided with the frequencies of maximum acoustic driving given by the model.

Original languageEnglish (US)
StatePublished - Jan 1 1995
Event31st Joint Propulsion Conference and Exhibit, 1995 - San Diego, United States
Duration: Jul 10 1995Jul 12 1995

Other

Other31st Joint Propulsion Conference and Exhibit, 1995
CountryUnited States
CitySan Diego
Period7/10/957/12/95

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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    Maskrey, A., Puissant, C., Glogowski, M., & Micci, M. M. (1995). Shear coaxial injector spray combustion experiments in a single element rocket chamber. Paper presented at 31st Joint Propulsion Conference and Exhibit, 1995, San Diego, United States.