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  • 1
    Electronic Resource
    Electronic Resource
    Hydrogen chloride chemical laser from hydrogen atom-chlorine azide reaction (1972)
    s.l. : American Chemical Society
    The @journal of physical chemistry 〈Washington, DC〉 76 (1972), S. 805-810 
    Details
    Source: ACS Legacy Archives
    Topics: Chemistry and Pharmacology , Physics
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1021/j100650a001
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    Paper (German National Licenses)
    Fulltext
  • 2
    Electronic Resource
    Electronic Resource
    Infrared and Phase Equilibria Studies of Intermolecular Compounds of Titanium Tetrachloride with Several Aromatic Hydrocarbons and Ethers (1964)
    s.l. : American Chemical Society
    The @journal of physical chemistry 〈Washington, DC〉 68 (1964), S. 2617-2621 
    Details
    Source: ACS Legacy Archives
    Topics: Chemistry and Pharmacology , Physics
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1021/j100791a038
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    Paper (German National Licenses)
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  • 3
    Electronic Resource
    Electronic Resource
    Plasma polymerization of ethane. I. Experimental studies of effluent gas composition and polymer deposition rates (1983)
    Springer
    Plasma chemistry and plasma processing 3 (1983), S. 139-161 
    Details
    ISSN: 1572-8986
    Keywords: RF plasma ; plasma polymerization ; gas chromatrography ; experimental
    Source: Springer Online Journal Archives 1860-2000
    Topics: Chemistry and Pharmacology , Mechanical Engineering, Materials Science, Production Engineering, Mining and Metallurgy, Traffic Engineering, Precision Mechanics , Technology
    Notes: Abstract The plasma polymerization of ethane was studied in a flow reactor of rectangular cross section. The plasma was sustained between parallel-plate electrodes by an RF generator operating at 13.56 MHz. The composition of the gas leaving the reactor was analyzed by gas chromatography. Polymer deposition rates were measured as a function of axial position in the reactor, using a quartz-crystal microbalance. The effluent gas is composed primarily of unreacted C2H6 and H2. Significant concentrations of CH4, C2H4, C2H2, and C3H8, and small amounts of C3H6, i-C5H12, and n-C5H12, are also observed. The distribution of these products is a strong function of the discharge power and of the gas pressure and residence time in the plasma. These experimental variables also affect both the rate of polymer deposition and the shape of the deposition profile along the reactor axis.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1007/BF00566018
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    Paper (German National Licenses)
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  • 4
    Electronic Resource
    Electronic Resource
    Plasma polymerization of ethane. II. Theoretical analysis of effluent gas composition and polymer deposition rates (1983)
    Springer
    Plasma chemistry and plasma processing 3 (1983), S. 163-192 
    Details
    ISSN: 1572-8986
    Keywords: RF plasma ; plasma polymerization ; modeling ; theoretical
    Source: Springer Online Journal Archives 1860-2000
    Topics: Chemistry and Pharmacology , Mechanical Engineering, Materials Science, Production Engineering, Mining and Metallurgy, Traffic Engineering, Precision Mechanics , Technology
    Notes: Abstract A theoretical model has been developed to describe the deposition of polymer occurring in a capacitatively coupled, low-pressure, RF discharge sustained in ethane. The reaction mechanism chosen for this model assumes that polymer formation is controlled by the formation of free radicals in the plasma and the subsequent reaction of these species at the surface of the electrodes used to sustain the plasma. Convective and diffusive transport is taken to occur in the direction parallel to the electrodes. Diffusive transport perpendicular to the electrodes is considered to be rapid, and hence the gradients in this direction are taken to be negligible. Both the composition of the gas leaving the plasma reactor and the axial profile of polymer deposition rate within the reactor, observed experimentally, are predicted accurately by the model. Results obtained from the model have also been used to estimate the kinetic chain length and degree of unsaturation in the polymer. Both predictions are found to be in reasonable agreement with experimental observations.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1007/BF00566019
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    Paper (German National Licenses)
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  • 5
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    Two successful geomagnetic-field-line tracing experiments (1972)
    American Geophysical Union
    Details
    Publication Date: 1972-06-01
    Print ISSN: 0148-0227
    Electronic ISSN: 2156-2202
    Topics: Geosciences
    Published by American Geophysical Union
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    PAPER CURRENT
  • 6
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    Costs and benefits to industry of online literature searches (1980)
    In:  Other Sources
    Details
    Publication Date: 2011-08-17
    Description: A description is given of a client survey conducted by the NASA Industrial Application Center, U.S.C., examining user-identified dollar costs and benefits of an online computerized literature search. Telephone interviews were conducted on a random sample of clients using a Denver Research Institute questionnaire. Of the total 159 clients surveyed, over 53% identified dollar benefits. A direct relationship between client dollars invested and benefits derived from the search was shown. The ratio of dollar benefit to investment dollar averaged 2.9 to 1. Precise data on the end user's evaluation of the dollar value of an information search are presented.
    Keywords: DOCUMENTATION AND INFORMATION SCIENCE
    Type: Special Libraries; 71; July 198
    Format: text
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    NASA TECHNICAL REPORTS
  • 7
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    Non-intrusive measurements in a rocket engine combustor (1993)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: In recent years analytical tools to characterize combustor flow have been developed in order to support design. To facilitate anchoring of combustion related physical models and the CFD codes in which they are incorporated, considerable development and application of non-intrusive combustion diagnostic capabilities has occurred. Raman spectroscopy can be used to simultaneously detect all polyatomic molecules present in significant concentrations and to determine gas temperature. This is because all molecules possess a distinct temperature dependent Raman spectrum. A multi-point diagnostic system for non-intrusive temperature and species profiling in rocket engines has been developed at Rocketdyne. In the present effort, the system has been undergoing validation for application to rocket engine component testing. A 4 inch diameter windowed combustor with a coaxial gas-gas injector was chosen for this series of validation experiments. Initially an excimer-pumped tunable dye laser and later a solid state Nd-Yag laser served as excitation sources. The Raman signal was dispersed by a monochromator and detected by a gated, intensified Charged Coupled Device (CCD) array. Experiments were carried out prior to each series of hot fire tests to ensure that the Raman signal detected was due to a spontaneous rather than a stimulated Raman emission process. Over sixty hot fire tests were conducted during the first series of tests with the excimer/dye laser. All hot fire testing was at a mixture ratio of 0.5 and chamber pressures of approximately 100 and approximately 300 psia. The Raman spectra of hydrogen, water vapor and oxygen recorded during single element hot fire tests were reduced and analyzed. A significant achievement was the attainment of single shot Raman spectra in cold flow tests. Unfortunately, the single shot signal-to-noise ratio deteriorated to an unacceptable level during the hot fire testing. Attempts to obtain temperature data from the hydrogen Q1-branch profiles obtained in hot fire tests suggest that potentially complicating factors may render the approach of averaging data on the photodiode array invalid. A second series of hot fire tests was conducted with a 4 element coaxial injector using the Nd-Yag laser. A very compact and portable diagnostics set up was assembled for ease of alignment, relocation and flexibility. Measurements were made at several regions in the chamber in order to map concentration profiles. High spatial resolution and improved signal to noise characteristics were demonstrated.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Marshall Space Flight Center, Eleventh Workshop for Computational Fluid Dynamic Applications in Rocket Propulsion; p 1619-1634
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Numerical analysis of SSME preburner injector atomization and combustion processes (1986)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The coaxial spray injection and combustion flowfields of a Space Shuttle Main Engine preburner injector element have been analyzed using a three-phase numerical code. The processes of atomization, evaporation, secondary droplet breakup, and multispecies chemistry, as well as turbulent diffusion, are included. The model produced realistic pictures of the complex internal flowfield, including liquid jet length, spray shape, flame-zone size and characteristics, and predicted temperatures that seem to be in agreement with test data envelopes. It predicted an external group combustion type of flame. Salient combustion and mixing features are discussed and sources of uncertainty are pointed out for future studies.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 86-0454
    Format: text
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    NASA TECHNICAL REPORTS
  • 9
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    Modeling of dense sprays from LOX/H2 coaxial injectors under supercritical conditions (1985)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Assumptions commonly employed in the analytical description of a thin spray become unacceptable as the droplet density and droplet volume displacement become large. Changes in the semiempirical models describing drop-drop or drop-gas interactions as well as in the basic modeling approach itself may be necessary. A number of efforts undertaken to improve such models of the atomization-evaporation process to render them applicable in the dense-spray, supercritical regime are described. The improvements include those for variable drop density, supercritical properties, stripping evaporation and drop reincorporation into the liquid stream. The models are developed for use with the ARICC three-phase finite difference combustion code. Selected results from a sample calculation are presented, demonstrating the enhanced realism achievable with the upgraded models.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: JHU, The 22nd JANNAF Combustion Meeting, Vol. 1; p 463-471
    Format: text
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    NASA TECHNICAL REPORTS
  • 10
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    SSME fuel preburner phase 1/phase 2+ comparison (1985)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: An analytical comparison of the predicted combustion flowfields for the Phase 1 and Phase 2+ fuel preburner configurations using an advanced CFD combustion code is currently underway at Rocketdyne. The Phase 2+ injector has a modified element design. The redesigned element provides for improved atomization through a shift in the injector element/face bleed flow split while maintaining an acceptable pressure drop. Cold-flow tests of the new design have been encouraging. As a complement to those tests, the Advanced Rocket Injector Combustor Code (ARICC) was selected to conduct a detailed combustion flowfield simulation. ARICC models two-dimensional (or axisymmetric), transient, turbulent, two-phase mixing and combustion flowfields. It is derived from a member of the Los Alamos ICEd-ALE family of codes. Unique features of ARICC include explicit representation of the coaxial LOX jet and hydrogen gas flows, distributed atomization processes, droplet breakup, and supercritical vaporation processes. Predictions of temperature and OH concentration profiles for the Phase 1 and Phase 2+ injector flowfields indicate a trend toward more uniform temperature distributions and shorter flame lengths with the Phase 2+ design.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: JHU, The 22nd JANNAF Combustion Meeting, Vol. 1; p 473-476
    Format: text
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    NASA TECHNICAL REPORTS
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