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  • 1
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    Measurement of the turbulence in a gaseous rocket combustion chamber☆ (1978)
    Elsevier
    Details
    Publication Date: 1978-01-01
    Print ISSN: 0010-2180
    Electronic ISSN: 1556-2921
    Topics: Energy, Environment Protection, Nuclear Power Engineering
    Published by Elsevier
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    PAPER CURRENT
  • 2
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    Turbulence in a gaseous hydrogen-liquid oxygen rocket combustion chamber (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The intensity of turbulence and the Lagrangian correlation coefficient for a LOX-GH2 rocket combustion chamber was determined from experimental measurements of tracer gas diffusion. A combination of Taylor's turbulent diffusion theory and a numerical method for solving the conservation equations of fluid mechanics was used to calculate these quantities. Taylor's theory was extended to consider the inhomogeneity of the turbulence field in the axial direction of the combustion chamber, and an exponential function was used to represent the Lagrangian correlation coefficient. The results indicate that the value of the intensity of turbulence reaches a maximum of 14% at a location about 7" downstream from the injector. The Lagrangian correlation coefficient associated with this value is given by the above exponential expression where alpha = 10,000/sec.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-134909
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Experimental determination of turbulence in a GH2-GOX rocket combustion chamber (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The intensity of turbulence and the Lagrangian correlation coefficient for a gaseous rocket combustion chamber have been determined from the experimental measurements of the tracer gas diffusion. A combination of Taylor's turbulent diffusion theory and Spalding's numerical method for solving the conservation equations of fluid mechanics was used to calculate these quantities. Taylor's theory was extended to consider the inhomogeneity of the turbulence field in the axial direction of the combustion chamber. An exponential function was used to represent the Lagrangian correlation coefficient. The results indicate that the maximum value of the intensity of turbulence is about 15% and the Lagrangian correlation coefficient drops to about 0.12 in one inch of the chamber length.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-CR-134672
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Convective heat transfer in the base region of large space boosters with clustered engines. (1967)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: Flow equations for convective heating associated with recirculating flow in clustered engine boosters for free viscous shear layer along exhaust jet boundary
    Keywords: AERODYNAMICS
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    Measurement of the turbulence in a gaseous rocket combustion chamber (1978)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: The intensity of turbulence and the Lagrangian correlation coefficient in a gaseous hydrogen (GH2)-gaseous oxygen (GOX) rocket combustion chamber are studied. A helium tracer gas was injected at an upstream point on the combustion chamber centerline. Samples collected downstream were analyzed for the spreading of the tracer gas concentration. Using Taylor's turbulent diffusion theory and Gosman's numerical method, turbulence parameters were found. In order to evaluate turbulence field inhomogeneity in the axial direction, Taylor's theory was extended. An exponential function was used to approximate the Lagrangian correlation coefficient. It was found that turbulence intensity varies from 15% near the injector to 4% at the nozzle entrance, and that the Lagrangian coefficient rapidly decreases when the dispersion time difference increases.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Combustion and Flame; 31; 2, 19; 1978
    Format: text
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    NASA TECHNICAL REPORTS
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