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  • PROPULSION SYSTEMS  (102)
  • 2020-2024
  • 2010-2014
  • 1970-1974  (102)
  • 1955-1959
  • 1945-1949
  • 1973  (102)
Collection
Keywords
Years
  • 2020-2024
  • 2010-2014
  • 1970-1974  (102)
  • 1955-1959
  • 1945-1949
Year
  • 1
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    Flight investigation of acoustic and thrust characteristics of several exhaust nozzles installed on underwing nacelles on an F106 airplane (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: To determine flyover noise and thrust and to investigate whether flight velocity significantly affects the noise of exhaust nozzles, a series of flight tests was conducted on three different exhaust nozzles of a type suitable for supersonic transport aircraft. The tests were conducted using an F-106B aircraft modified to carry two underwing nacelles, each containing a calibrated turbojet engine. A flyover altitude of 91 meters (300 ft) and a Mach number of 0.4 provided acoustic data that were repeatable to within + or -1.5 PNdB. Flyover results showed that an auxiliary inlet ejector nozzle was the quietest of the nozzles tested; flight velocity appeared to reduce its noise.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-TM-X-2854 , E-7319
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Program user's manual for optimizing the design of a liquid or gaseous propellant rocket engine with the automated combustor design code AUTOCOM (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: This computer program manual describes in two parts the automated combustor design optimization code AUTOCOM. The program code is written in the FORTRAN 4 language. The input data setup and the program outputs are described, and a sample engine case is discussed. The program structure and programming techniques are also described, along with AUTOCOM program analysis.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-CR-2293
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Exploratory development of a glass ceramic automobile thermal reactor (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: This report summarizes the design, fabrication and test results obtained for glass-ceramic (CER-VIT) automotive thermal reactors. Several reactor designs were evaluated using both engine-dynamometer and vehicle road tests. A maximum reactor life of about 330 hours was achieved in engine-dynamometer tests with peak gas temperatures of about 1065 C (1950 F). Reactor failures were mechanically induced. No evidence of chemical degradation was observed. It was concluded that to be useful for longer times, the CER-VIT parts would require a mounting system that was an improvement over those tested in this program. A reactor employing such a system was designed and fabricated.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-CR-134513
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Dynamic response of Mach 2.5 axisymmetric inlet with 40 percent supersonic internal area contraction (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Results of experimental tests conducted on a supersonic, mixed compression, axisymmetric inlet are presented. The inlet is designed for operation at Mach 2.5 with a turbofan engine (TF-30). The inlet was terminated with either a choked-orifice plate or a long pipe with variable area choked exit plug. Frequency responses were obtained for selected static pressures in the diffuser. These pressures were selected as potential control signals for terminal shock control. Frequency responses were obtained for the Mach 2 and 2.5 conditions for different terminations. Responses also were obtained with and without cowl bleed. Internal disturbances were produced by sinusoidally varying the inlet overboard bypass doors at frequencies out to 100 hertz.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-TM-X-2833 , E-7426
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Solar electric propulsion/instrument/subsystems interaction study (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The interactive effects between a solar electric propulsion system and an electrically propelled scientific spacecraft were examined. The operation of the ion thrusters may impact upon the acquisition and interpretation of data by the science payload of the spacecraft. The effluents from the operation of the electric propulsion unit may also impact upon the operation of the various subsystems of the vehicle. Specific interactive effects were isolated where meaningful levels of interaction may occur. The level of impact upon elements of the science payload and other affected subsystems is examined, and avenues for the reduction or elimination of impact are defined.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-CR-114732 , TRW-22878-6007-RU-00
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Plume mass flow and optical damage distributions for an MMH/N2O4 RCS thruster (1973)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The data obtained from two recent experiments conducted in a continuing series of experiments at the Lewis Research Center into the contamination characteristics of a 5-pound thrust MMH/N2O4 engine are presented. The primary objectives of these experiments were to establish the angular distribution of condensible exhaust products within the plume and the corresponding optical damage angular distribution of transmitting optical elements attributable to this contaminant. The plume mass flow distribution was measured by five quartz crystal microbalances (QCM's) located at the engine axis evaluation. The fifth QCM was located above the engine and 15 deg behind the nozzle exit plane. The optical damage was determined by ex-situ transmittance measurements for the wavelength range from 0.2 to 0.6 microns on 2.54 cm diameter fused silica discs also located at engine centerline elevation. Both the mass deposition and optical damage angular distributions followed the expected trend of decreasing deposition and damage as the angle between sensor or sample and the nozzle axis increased. A simple plume gas flow equation predicted the deposition distribution reasonably well for angles of up to 55 degrees. The optical damage measurements also indicated significant effects at large angles.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-TM-X-71465 , Space Simulation Conf.; Nov 12, 1973 - Nov 14, 1973; Los Angeles
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Parametric test results of a swirl-can combustor. (1973)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Pollutant levels of oxides of nitrogen, unburned hydrocarbons, and carbon monoxide were measured for three models of an experimental, annular swirl can combustor. The combustor was 1.067 meters in outer diameter, incorporated 120 modules, and was specifically designed for elevated exit temperature performance. Test conditions included combustor inlet temperatures of 589, 756, and 839 K, inlet pressures of 3 to 6.4 atmospheres, reference velocities of 21 to 38 meters per second, and combustor equivalence ratios, based on total combustor flows, of 0.206 to 1.028. Maximum oxides of nitrogen emission index values occurred at an equivalence ratio of 0.7 with lower values measured for both higher and lower equivalence ratios.
    Keywords: PROPULSION SYSTEMS
    Type: National Meeting; Jun 04, 1973 - Jun 06, 1973; Detroit, MI
    Format: text
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    NASA TECHNICAL REPORTS
  • 8
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    Reliability and effective thermal conductivity of three metallic-ceramic composite insulating coatings on cooled hydrogen-oxygen rockets (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An experimental investigation of the structural integrity and effective thermal conductivity of three metallic-ceramic composite coatings was conducted. These coatings were plasma sprayed onto the combustion side of water-cooled, 12.7-centimeter throat diameter, hydrogen-oxygen rocket thrust chambers operating at 2.07 to 4.14 meganewtons per square meter chamber pressure. The metallic-ceramic composites functioned for six to 17 cycles and for as long as 213 seconds of rocket operations and could have probably provided their insulating properties for many additional cycles. The effective thermal conductivity of all the coatings was in the range of 0.7472 to 4.483 w/(m)(K), which makes the coatings a very effective thermal barrier. Photomicrographic studies of cross-sectioned coolant tubes seem to indicate that the effective thermal conductivity of the coatings is controlled by contact resistance between the particles, as a result of the spraying process, and not the thermal conductivity of the bulk materials.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-TN-D-7392 , E-7461
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    Theoretical studies of tone noise from a fan rotor (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An analytical study was made of some possible rotor alone noise sources of dipole, quadrapole and monopole characters which generate discrete tone noise. Particular emphasis is given to the tone noise caused by fan inlet flow distortion and turbulence. Analytical models are developed to allow prediction of absolute levels. Experimental data measured on a small scale fan is presented which indicates inlet turbulence interaction with a fan rotor can be a source of tone noise. Predicted and measured tone noise for the small scale rotor are shown to be in reasonable agreement.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-CR-2354
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    Experimental investigation of aerodynamic performance of cooled turbine vanes at gas- to collant-temperature ratios up to 2.75 (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The results of an experimental investigation of the aerodynamic performance of two geometrically similar turbine vanes with different cooling designs are presented. The test vanes were a convection-film-cooled vanes and a transpiration-cooled vane. A solid uncooled vane with the same aerodynamic profile as the cooled vane was also tested. Four vanes of each type were tested in an annular sector cascade. The cooled vanes were tested at primary to coolant temperature ratios of 1.0, 1.75, and 2.75 and a coolant to primary pressure ratios of 1.0, 1.2, and 1.5. This resulted in coolant flows up to about 10 percent of the primary flow. The principal measurements were surveys of vane exit total pressure, total temperature, and static pressure. The report includes a brief description of the test facility and the design of the test vanes. The test results presented include weight flow and efficiency data for the uncooled vanes and coolant flow, primary flow, and efficiency data as functions of the cooling variables for the cooled vanes.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-TM-X-2733 , E-7183
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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