Unsteady hot fire atomization measurements in injector sprays

Michael Matthew Micci, R. J. Kujala, D. Gandilhon, M. Ferraro, M. G. Schmidt

Research output: Contribution to conferencePaper

Abstract

Acoustic oscillations were induced in a sub-scale liquid rocket engine that burned liquid oxygen and gaseous hydrogen as propellants. The oscillations in the chamber were forced by a rotating gear just downstream of the nozzle throat. High frequency data was acquired for pressure and velocity via a pressure transducer and a magnetic flowmeter. A cross correlation was performed on the velocity and pressure signals to determine the amplitude and phase difference of the two signals. An linearized onedimensional acoustic model was developed to simulate the mean and unsteady flow within the chamber with mass and energy addition. The phase difference between unsteady pressure and velocity was determined from the model and fit to match the phase difference measured by the experiments. The points where the modeled and experimental phase differences agreed determined the real part of the propellant evaporation and combustion pressure- and velocity-coupled response functions.

Original languageEnglish (US)
StatePublished - Jan 1 1997
Event33rd Joint Propulsion Conference and Exhibit, 1997 - Seattle, United States
Duration: Jul 6 1997Jul 9 1997

Other

Other33rd Joint Propulsion Conference and Exhibit, 1997
CountryUnited States
CitySeattle
Period7/6/977/9/97

Fingerprint

Atomization
Fires
Propellants
Magnetic flowmeters
Acoustics
Pressure transducers
Rocket engines
Liquids
Unsteady flow
Gears
Nozzles
Evaporation
Hydrogen
Oxygen
Experiments

All Science Journal Classification (ASJC) codes

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

Cite this

Micci, M. M., Kujala, R. J., Gandilhon, D., Ferraro, M., & Schmidt, M. G. (1997). Unsteady hot fire atomization measurements in injector sprays. Paper presented at 33rd Joint Propulsion Conference and Exhibit, 1997, Seattle, United States.
Micci, Michael Matthew ; Kujala, R. J. ; Gandilhon, D. ; Ferraro, M. ; Schmidt, M. G. / Unsteady hot fire atomization measurements in injector sprays. Paper presented at 33rd Joint Propulsion Conference and Exhibit, 1997, Seattle, United States.
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Micci, MM, Kujala, RJ, Gandilhon, D, Ferraro, M & Schmidt, MG 1997, 'Unsteady hot fire atomization measurements in injector sprays' Paper presented at 33rd Joint Propulsion Conference and Exhibit, 1997, Seattle, United States, 7/6/97 - 7/9/97, .

Unsteady hot fire atomization measurements in injector sprays. / Micci, Michael Matthew; Kujala, R. J.; Gandilhon, D.; Ferraro, M.; Schmidt, M. G.

1997. Paper presented at 33rd Joint Propulsion Conference and Exhibit, 1997, Seattle, United States.

Research output: Contribution to conferencePaper

TY - CONF

T1 - Unsteady hot fire atomization measurements in injector sprays

AU - Micci, Michael Matthew

AU - Kujala, R. J.

AU - Gandilhon, D.

AU - Ferraro, M.

AU - Schmidt, M. G.

PY - 1997/1/1

Y1 - 1997/1/1

N2 - Acoustic oscillations were induced in a sub-scale liquid rocket engine that burned liquid oxygen and gaseous hydrogen as propellants. The oscillations in the chamber were forced by a rotating gear just downstream of the nozzle throat. High frequency data was acquired for pressure and velocity via a pressure transducer and a magnetic flowmeter. A cross correlation was performed on the velocity and pressure signals to determine the amplitude and phase difference of the two signals. An linearized onedimensional acoustic model was developed to simulate the mean and unsteady flow within the chamber with mass and energy addition. The phase difference between unsteady pressure and velocity was determined from the model and fit to match the phase difference measured by the experiments. The points where the modeled and experimental phase differences agreed determined the real part of the propellant evaporation and combustion pressure- and velocity-coupled response functions.

AB - Acoustic oscillations were induced in a sub-scale liquid rocket engine that burned liquid oxygen and gaseous hydrogen as propellants. The oscillations in the chamber were forced by a rotating gear just downstream of the nozzle throat. High frequency data was acquired for pressure and velocity via a pressure transducer and a magnetic flowmeter. A cross correlation was performed on the velocity and pressure signals to determine the amplitude and phase difference of the two signals. An linearized onedimensional acoustic model was developed to simulate the mean and unsteady flow within the chamber with mass and energy addition. The phase difference between unsteady pressure and velocity was determined from the model and fit to match the phase difference measured by the experiments. The points where the modeled and experimental phase differences agreed determined the real part of the propellant evaporation and combustion pressure- and velocity-coupled response functions.

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Micci MM, Kujala RJ, Gandilhon D, Ferraro M, Schmidt MG. Unsteady hot fire atomization measurements in injector sprays. 1997. Paper presented at 33rd Joint Propulsion Conference and Exhibit, 1997, Seattle, United States.