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  • 1
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    Large Deflection of curved plates (1956)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Type: NACA-TN-3684
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Bending of thin plates with compound curvature (1952)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Type: NACA-TN-2782
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Low NOx heavy fuel combustor concept program. Phase 1: Combustion technology generation (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The viability of low emission nitrogen oxide (NOx) gas turbine combustors for industrial and utility application. Thirteen different concepts were evolved and most were tested. Acceptable performance was demonstrated for four of the combustors using ERBS fuel and ultralow NOx emissions were obtained for lean catalytic combustion. Residual oil and coal derived liquids containing fuel bound nitrogen (FBN) were also used at test fuels, and it was shown that staged rich/lean combustion was effective in minimizing the conversion of FBN to NOx. The rich/lean concept was tested with both modular and integral combustors. While the ceramic lined modular configuration produced the best results, the advantages of the all metal integral burners make them candidates for future development. An example of scaling the laboratory sized combustor to a 100 MW size engine is included in the report as are recommendations for future work.
    Keywords: ENERGY PRODUCTION AND CONVERSION
    Type: NASA-CR-165482 , DOE/NASA/0146-1 , NAS 1.26:165482
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    NASA TECHNICAL REPORTS
  • 4
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    Investigation of the Ignition and Burning of Materials in Space Cabin Atmospheres. Part 2: Ignition of a Combustible Mixture by a Hot Body with the Effects of Gravity (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The ignition of a combustible gas mixture by a hot cylinder under the effect of a gravity field for steady state conditions is examined. For this purpose a horizontal cylinder is considered with gravity as a parameter together with a finite chemical reacting flow generated by free convection with the additional effect of diffusion. Both mass transfer and zero mass transfer cases are considered. By defining an ignition criterion the surface temperature and species are obtained from the analysis as a function of the gravity field. It is supposed that at the point of ignition the heat evolved in the gas is sufficiently high to attain a sustained combustion without any energy from the hot cylinder.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-CR-128064 , GE-TIS-72SD2061-PT-2
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Investigation of the Ignition and Burning of Materials in Space Cabin Atmospheres. Part 1: Ignition and Burning of Material (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An analytical study of the theory of ignition and burning of a plastic material immersed in an atmosphere of a space cabin which may be subjected to gravity force changes is considered. The hazardous condition in a space cabin environment where the changes of gravity may effect the combustion process is evaluated. The model considered the analysis of the coupled gas and solid phases and is based on the premise that material heating leads to the formation of pyrolysis gases from the decomposed solid which then react with the ambient oxidizer to further the combustion process. Moreover, free convection plays a dominant role in transporting these hot gases to the virgin material. A time-dependent study of the coupled gas-solid model as required for ignition processes with emphasis on the surface energy interchange of the gas and solid phases has been made. Detailed distribution of species composition and temperature patterns provide a spatial and time map of the evolving gases from the material combustion.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-CR-128068 , GE-TIS-72SD2061-PT-1
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Low NO/x/ and fuel flexible gas turbine combustors (1981)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The feasibility of various low NO(x) emission gas turbine combustor configurations was evaluated. The configurations selected for fabrication and testing at full pressure and temperature involved rich-lean staged combustion utilizing diffusion flames, rich-lean prevaporized/premix flames, and staged catalytic combustion. The test rig consisted of a rich burner module, a quench module, and a lean combustion module. Test results are obtained for the combustor while burning petroleum distillate fuel, a coal derived liquid, and a petroleum residual fuel. The results indicate that rich-lean diffusion flames with low fuel-bound nitrogen conversion are achievable with very high combustion efficiencies.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: ASME PAPER 81-GT-99 , Gas Turbine Conference and Products Show; Mar 09, 1981 - Mar 12, 1981; Houston, TX
    Format: text
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    NASA TECHNICAL REPORTS
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