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

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

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 conference › Paper › peer-review

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 language	English (US)
State	Published - 1995
Event	31st Joint Propulsion Conference and Exhibit, 1995 - San Diego, United States Duration: Jul 10 1995 → Jul 12 1995

Other

Other	31st Joint Propulsion Conference and Exhibit, 1995
Country/Territory	United States
City	San Diego
Period	7/10/95 → 7/12/95

All Science Journal Classification (ASJC) codes

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

Cite this

@conference{d4810d46641f453eb2e93ab4e3d13d52,

title = "Shear coaxial injector spray combustion experiments in a single element rocket chamber",

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.",

author = "A. Maskrey and C. Puissant and M. Glogowski and Micci, {M. M.}",

note = "Funding Information: This work was supported by AFOSR Graut F49620-93-1-0126 and NASA Grant NAGW-1356, Supplement 6. C. Puissant wishes to acknowledge the financial support of the Societe Europeene de Propulsion. Publisher Copyright: {\textcopyright} 1995, American Institute of Aeronautics and Astronautics, Inc. All rights reserved.; 31st Joint Propulsion Conference and Exhibit, 1995 ; Conference date: 10-07-1995 Through 12-07-1995",

year = "1995",

language = "English (US)",

}

TY - CONF

T1 - Shear coaxial injector spray combustion experiments in a single element rocket chamber

AU - Maskrey, A.

AU - Puissant, C.

AU - Glogowski, M.

AU - Micci, M. M.

N1 - Funding Information: This work was supported by AFOSR Graut F49620-93-1-0126 and NASA Grant NAGW-1356, Supplement 6. C. Puissant wishes to acknowledge the financial support of the Societe Europeene de Propulsion. Publisher Copyright: © 1995, American Institute of Aeronautics and Astronautics, Inc. All rights reserved.

PY - 1995

Y1 - 1995

N2 - 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.

AB - 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.

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M3 - Paper

AN - SCOPUS:84964545049

T2 - 31st Joint Propulsion Conference and Exhibit, 1995

Y2 - 10 July 1995 through 12 July 1995

ER -

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

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