Combustion performance of RP-1/GO2/GH2 Tripropellants

M. G. Schmidt, Michael Matthew Micci

Research output: Contribution to conferencePaper

Abstract

An experimental investigation was conducted to evaluate the combustion performance and stability of injecting gaseous hydrogen during the combustion of RP-1 and gaseous oxygen in a rocket combustion chamber. A single, tripropellant, swirl coaxial injection element fed a 1 inch hexagonal crosssection chamber of heat-sink design. Modular injector allowed control of the momentum ratios and subsequent atomization and mixing of the propellants. 84 tests were completed at various mixture ratios, injection velocities, and chamber pressures, with and without the addition of 10% hydrogen per total fuel mass. The combustion performance (c*), combustion efficiency (ηc*), and high frequency dynamic chamber pressure were recorded. The injection of 10% hydrogen to the RP-1/O2 combustion was shown to increase the efficiency, improve stability and decrease soot. Results from the rocket combustor hotfire testing showed an average increase in combustion efficiency from 92% to 97% under similar operating conditions. High frequency pressure measurements in the combustion chamber indicated a pronounced drop in the acoustic intensity. The total acoustic power was reduced by a factor of 9. The average power spectral density (PSD) at the first longitudinal chamber frequency was reduced from 1.10 to 0.15 [psi-rms2/Hz]. In addition to these results, soot accumulation on the chamber walls and in the exhaust plume was greatly reduced with the addition of the hydrogen. Correlation of the results on the basis of injector type, hydrogen injection location, and injection momentum indicate a change in the RP-1/O2 chemical kinetics occurred with the addition of hydrogen.

Original languageEnglish (US)
Pages1-8
Number of pages8
StatePublished - Jan 1 1998
Event34th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, 1998 - Cleveland, United States
Duration: Jul 13 1998Jul 15 1998

Other

Other34th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, 1998
CountryUnited States
CityCleveland
Period7/13/987/15/98

Fingerprint

Hydrogen
Soot
Combustion chambers
Rockets
Momentum
Acoustic intensity
Power spectral density
Heat sinks
Atomization
Propellants
Pressure measurement
Combustors
Reaction kinetics
Acoustics
Oxygen
Testing

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

Schmidt, M. G., & Micci, M. M. (1998). Combustion performance of RP-1/GO2/GH2 Tripropellants. 1-8. Paper presented at 34th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, 1998, Cleveland, United States.
Schmidt, M. G. ; Micci, Michael Matthew. / Combustion performance of RP-1/GO2/GH2 Tripropellants. Paper presented at 34th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, 1998, Cleveland, United States.8 p.
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Schmidt, MG & Micci, MM 1998, 'Combustion performance of RP-1/GO2/GH2 Tripropellants' Paper presented at 34th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, 1998, Cleveland, United States, 7/13/98 - 7/15/98, pp. 1-8.

Combustion performance of RP-1/GO2/GH2 Tripropellants. / Schmidt, M. G.; Micci, Michael Matthew.

1998. 1-8 Paper presented at 34th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, 1998, Cleveland, United States.

Research output: Contribution to conferencePaper

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Schmidt MG, Micci MM. Combustion performance of RP-1/GO2/GH2 Tripropellants. 1998. Paper presented at 34th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, 1998, Cleveland, United States.