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  • AIRCRAFT PROPULSION AND POWER  (11)
  • ENERGY PRODUCTION AND CONVERSION  (10)
  • PROPULSION SYSTEMS  (2)
  • 1
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    NASA Lewis Research Center combustion MHD experiment (1982)
    In:  Other Sources
    Details
    Publication Date: 2019-01-25
    Description: The MHD power generation experiments were conducted in a high field strength cryomagnet which was adapted from an existing facility. In its original construction, it consisted of 12 high purity aluminum coils pool cooled in a bath of liquid neon. In this configuration, a peak field of 15 tesla was produced. For the present experiments, the center four coils were removed and a 23 cm diameter transverse warm bore tube was inserted to allow the placement of the MHD experiment between the remaining eight coils. In this configuration, a peak field of 6 tesla should be obtainable. The time duration of the experiment is limited by the neon supply which allows on the order of 1 minute of total operating time followed by an 18-hour reliquefaction period. As a result, the experiments are run in a pulsed mode. The run duration for the data presented here was 5 sec. The magnetic field profile along the MHD duct is shown. Since the working fluid is in essence superheated steam, it is easily water quenched at the exit of the diffuser and the components are designed vacuum tight so that the exhaust pipe and demister an be pumped down to simulate the vacuum of outer space.
    Keywords: ENERGY PRODUCTION AND CONVERSION
    Type: R and D Associates Proc. of the AFOSR Spec. Conf. on Prime-Power for High Energy Space Systems, Vol. 1; 10 p
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Performance of semi-transportation-cooled liner in high-temperature-rise combustors (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Results from tests with the Lamilloy combustor liner are compared with results obtained from a conventionally designed, film cooled, step-louver liner. Operation of the Lamilloy liner with counterrotating swirl combustor fuel modules with mixing venturis was possible to a fuel-air ratio of 0.065 without obtaining excessive liner metal temperatures. At the 0.065 fuel-air condition the average liner metal temperature was 140 K and the maximum local temperature 280 K above the inlet air temperature. Combustion efficiency, pattern factor, and smoke data are discussed.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TP-1806 , E-494
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Quantitative analysis of defects in silicon. Silicon sheet growth development for the large are silicon sheet task of the low-cost solar array project (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: One hundred and seventy four silicon sheet samples were analyzed for twin boundary density, dislocation pit density, and grain boundary length. Procedures were developed for the quantitative analysis of the twin boundary and dislocation pit densities using a QTM-720 Quantitative Image Analyzing system. The QTM-720 system was upgraded with the addition of a PDP 11/03 mini-computer with dual floppy disc drive, a digital equipment writer high speed printer, and a field-image feature interface module. Three versions of a computer program that controls the data acquisition and analysis on the QTM-720 were written. Procedures for the chemical polishing and etching were also developed.
    Keywords: ENERGY PRODUCTION AND CONVERSION
    Type: NASA-CR-163140 , MRI-276 , DOE/JPL-954977-79/9
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    NASA TECHNICAL REPORTS
  • 4
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    Analysis of defect structure in silicon. Silicon sheet growth development for the large area silicon sheet task of the Low-Cost Solar array Project (1982)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: One hundred ninety-three silicon sheet samples, approximately 880 square centimeters, were analyzed for twin boundary density, dislocation pit density, and grain boundary length. One hundred fifteen of these samples were manufactured by a heat exchanger method, thirty-eight by edge defined film fed growth, twenty-three by the silicon on ceramics process, and ten by the dendritic web process. Seven solar cells were also step-etched to determine the internal defect distribution on these samples. Procedures were developed or the quantitative characterization of structural defects such as dislocation pits, precipitates, twin & grain boundaries using a QTM 720 quantitative image analyzing system interfaced with a PDP 11/03 mini computer. Characterization of the grain boundary length per unit area for polycrystalline samples was done by using the intercept method on an Olympus HBM Microscope.
    Keywords: ENERGY PRODUCTION AND CONVERSION
    Type: NASA-CR-169058 , DOE/JPL-955676-1 , JPL-9950-677 , NAS 1.26:169058 , MRI-289
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    NASA TECHNICAL REPORTS
  • 5
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    Performance of a short annular dump diffuser using suction-stabilized vortices at inlet Mach numbers to 0.41 (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A short, annular dump diffuser was designed to use suction to establish stabilized vortices on both walls for improved flow expansion in the region of an abrupt area change. The diffuser was tested at near ambient inlet pressure and temperature. The overall diffuser area ratio was 4.0. The inlet height was 2.54 cm and the exit pitot-static rakes were located at a distance from the vortex fence equal to two or six times the inlet height. Performance data were taken at near ambient temperature and pressure for nominal inlet Mach numbers of 0.18 to 0.41 with suction rates of 0 to 18 percent of the total inlet airflow. The exit velocity profile could be shifted toward either wall by adjusting the inner- or outer-wall suction rate. Symmetrical exit velocity profiles were unstable, with a tendency to shift back to hub- or tip-weighted profile. Diffuser effectiveness was increased from about 47 percent without suction to over 85 percent at a total suction rate of about 14 percent. The diffuser total pressure losses at inlet Mach numbers of 0.18 and 0.41 decreased from 1.1 and 5.6 percent without suction to 0.48 and 5.2 percent at total suction rates of 14.4 and 5.6 percent, respectively.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TP-1194 , E-9332
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Performance of a vortex-controlled diffuser in an annular swirl-can combustor at inlet Mach numbers up to 0.53 (1979)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A short, annular dump diffuser with suction stabilized vortices in the region of abrupt area change was tested with a full scale, annular swirl can combustor. The prediffuser area ratio was 1.4. Performance data were obtained for both isothermal and burning conditions at inlet temperatures of 589 to 895 K and pressures of 0.5 to 1.0 MPa for a range of diffuser inlet Mach numbers from 0.25 to 0.53. Suction rates were 0 to 20 percent of the total diffuser mass flow rate. Diffuser effectiveness increased from 47 percent without suction to approximately 80 percent for a total suction rate of 14 percent. Combustor total pressure loss for the same total suction rate was reduced from 6.8 percent without suction to 4.0 percent at an inlet Mach number of 0.40.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TP-1452 , E-9832
    Format: application/pdf
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  • 7
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    Experimental investigation of the low NOx vortex airblast annular combustor (1984)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A low oxides of nitrogen vortex airblast annular combustor was evaluated which has attained the goal of 1 gm NO2/kg fuel or less during operation. The experimental combustor test conditions were a nominal inlet-air temperature of 703 K, inlet total pressures between 0.52 to 0.83 MPa, and a constant inlet Mach number of 0.26. Exit temperature pattern factors for all test points were between 0.16 and 0.20 and exit swirl flow angles were 47 degrees at isothermal conditions and 23 degrees during combustion. Oxides of nitrogen did not exceed 1.05 gm NO2/kg fuel at the highest inlet pressure and exhaust temperature tested. Previous correlations have related NOx proportionally to the combustor inlet pressure raised to some exponent. In this experiment, a band of exponents between 0.5 and 1.0 resulted for fuel-air ratios from 0.023 to 0.027 and inlet pressures from 0.52 to 0.83 MPa. Previously announced in STAR as N84-22567
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: AIAA PAPER 84-1170
    Format: text
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  • 8
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    Preliminary investigation of a two-zone swirl flow combustor (1984)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The effect of full-annular swirling-flow on a flow-zone combustor design is investigated. Swirl flow angles of 25, 35, and 45 degrees were investigated in a combustor design envelope typical of those used in modern engines. The two-zone combustor had 24 pilot-zone fuel injectors and 24 main-fuel injectors located in the centerbody between the pilot and swirl passage. Combustor performance was determined at idle, and two parametric 589 K inlet temperature conditions. Combustor performance was highest with the 45 degree swirl vane design; at the idle condition, combustion efficiency was 99.5 percent. The 45 degree swirl vane also produced the lowest pattern factor of the three angles and showed a combustor lean blowout limit below a 0.001 fuel-air ratio. Combustor total pressure drop varied from a low of 4.6 percent for the 25 degree swirl to a high of 4.9 percent for the 45 degree swirl. Previously announced in STAR as N84-22565
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: AIAA PAPER 84-1169
    Format: text
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  • 9
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    Velocity and temperature distributions of coal-slag layers on magnetohydrodynamic generators walls (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Approximate analytical expressions are derived for the velocity and temperature distributions in steady state coal slag deposits flowing over MHD generator walls. Effects of slag condensation and Joule heating are included in the analysis. The transport conditions and the slag temperature at the slag-gas interface are taken to be known parameters in the formulation. They are assumed to have been predetermined either experimentally or from the slag properties and the gas dynamic calculations of the free stream flow. The analysis assumes a power law velocity profile for the slag and accounts for the coupling between the energy and momentum conservation equations. Comparisons are made with the more exact numerical solutions to verify the accuracy of the results.
    Keywords: ENERGY PRODUCTION AND CONVERSION
    Type: NASA-TN-D-8396 , E-8929
    Format: application/pdf
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  • 10
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    Design and preliminary results of a semitranspiration cooled /Lamilloy/ liner for a high-pressure high-temperature combustor (1978)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A Lamilloy combustor liner has been designed, fabricated and tested in a combustor at pressures up to 8 atmospheres. The liner was fabricated of a three layer Lamilloy structure and designed to replace a conventional step-louver liner. The liner will be used in a combustor that provides hot gases to a turbine cooling test facility at pressures up to 40 atmospheres. The Lamilloy liner was tested extensively at lower pressures and demonstrated lower metal temperatures than the conventional liner, while at the same time requiring about 40 percent less cooling air flow. Tests conducted at combustor exit temperatures in excess of 2200 K have not indicated any cooling or durability problems with the Lamilloy liner.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: AIAA PAPER 78-997 , Joint Propulsion Conference; Jul 25, 1978 - Jul 27, 1978; Las Vegas, NV; US
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