Item Details

Frequency Response of a Vaporization Process to Distorted Acoustic Disturbances

by Marcus F. Heidmann
Format
Book; Government Document; Online; EBook
Published
Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1972.
Language
English
Series
NASA Technical Note
Summary
The open-loop response properties expressed as the mass vaporized in phase and out of phase with the pressure oscillations were numerically evaluated for a vaporizing n-heptane droplet. The evaluation includes the frequency dependence introduced by periodic oscillation in droplet mass and temperature. A given response was achieved over a much broader range of frequency with harmonically distorted disturbances than with sinusoidal disturbances. The results infer that distortion increases the probability of incurring spontaneous and triggered instability in any rocket engine combustor by broadening the frequency range over which the vaporization process can support an instability.
Description
32 p. : ill. ; 27 cm.
Mode of access: Internet.
Notes
  • Prepared at Lewis Research Center.
  • Cover title.
  • Bibliography: p. 32.
Series Statement
NASA technical note ; NASA TN D-6806
Logo for Copyright Not EvaluatedCopyright Not Evaluated
Technical Details

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    a| Frequency response of a vaporization process to distorted acoustic disturbances c| by Marcus F. Heidmann.
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    a| Washington, D.C. : b| National Aeronautics and Space Administration ; a| [Springfield, Va. : b| For sale by the National Technical Information Service], c| 1972.
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    a| 32 p. : b| ill. ; c| 27 cm.
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    0
      
    a| NASA technical note ; v| NASA TN D-6806
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    a| Prepared at Lewis Research Center.
    500
      
      
    a| Cover title.
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    a| Bibliography: p. 32.
    520
      
      
    a| The open-loop response properties expressed as the mass vaporized in phase and out of phase with the pressure oscillations were numerically evaluated for a vaporizing n-heptane droplet. The evaluation includes the frequency dependence introduced by periodic oscillation in droplet mass and temperature. A given response was achieved over a much broader range of frequency with harmonically distorted disturbances than with sinusoidal disturbances. The results infer that distortion increases the probability of incurring spontaneous and triggered instability in any rocket engine combustor by broadening the frequency range over which the vaporization process can support an instability.
    538
      
      
    a| Mode of access: Internet.
    650
      
    0
    a| Frequency response (Dynamics)
    650
      
    0
    a| Rocket engines x| Combustion.
    710
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    a| United States. b| National Aeronautics and Space Administration.
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    a| Lewis Research Center.
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