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  • PROPULSION SYSTEMS
  • 1970-1974  (147)
  • 1974  (147)
  • 1
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    Noncircular Orifice Holes and Advanced Fabrication Techniques for Liquid Rocket Injectors (Phases 1, 2, 3, and 4) (1974)
    In:  CASI
    Details
    Publication Date: 2019-07-20
    Description: A comprehensive summary of the results of a cold-flow and hot-fire experimental study of the mixing and atomization characteristics of injector elements incorporating noncircular orifices is presented. Both liquid/liquid and gas/liquid element types are discussed. Unlike doublet and triplet elements (circular orifices only) were investigated for the liquid/liquid case while concentric tube elements were investigated for the gas/liquid case. It is concluded that noncircular shape can be employed to significant advantage in injector design for liquid rocket engines.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-CR-134315 , R-9271
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Optimal rocket thrust profile shaping using third degree spline function interpolation (1974)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Optimal solid-rocket thrust profiles for the parallel-burn, solid-rocket-assisted space shuttle are investigated. Solid-rocket thrust profiles are simulated by using third-degree spline functions, with the values of the thrust ordinates defined as parameters. The profiles are optimized parametrically, using the Davidon-Fletcher-Powell penalty function method, by minimizing propellant weight subject to state and control inequality constraints and to terminal boundary conditions. This study shows that optimizing a control variable parametrically by using third-degree spline function interpolation allows the control to be shaped so that inequality constraints are strictly adhered to and all corners are eliminated. The absence of corners, which is realistic in nature, makes this method attractive from the viewpoint of solid rocket grain design.
    Keywords: PROPULSION SYSTEMS
    Type: AIAA PAPER 74-823 , Mechanics and Control of Flight Conference; Aug 05, 1974 - Aug 09, 1974; Anaheim, CA
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    An examination of injector/combustor design effects on scramjet performance (1974)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Description of a simplified one-dimensional treatment of fuel injection for supersonic combustor performance analysis. Representative mixing efficiency variations for both parallel and cross-stream injection are obtained, and approximate means for estimating the length required for complete mixing are demonstrated. Comparisons of calculated and measured data show good agreement.
    Keywords: PROPULSION SYSTEMS
    Type: International Symposium on Air Breathing Engines; Mar 24, 1974 - Mar 29, 1974; Sheffield
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Formulation of a distortion index based on peak compressor pressure ratios (1974)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: In order to effectively use a compressor face total-pressure distortion index as a measure of inlet-engine compatibility, a correlation of distortion amplitude with stall margin must be developed with minimal scatter. A recent analysis of data recorded in extensive distortion screen tests with the J85-GE-13 turbojet engine has resulted in a correlation based on compressor discharge pressure ratioed to the minimum pressure at the compressor face. Simply by determining compressor stall lines with a single hub radial distortion pattern, a single tip radial pattern, and with undistorted inflow, the overall compressor pressure ratio at stall for even the most complex distortion pattern was found to be predictable.
    Keywords: PROPULSION SYSTEMS
    Type: National Conference on Environmental Effects on Aircraft and Propulsion Systems; May 21, 1974 - May 23, 1974; Trenton, NJ
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    Diffusive ignition and combustion in a wall jet (1974)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Hydrogen is injected from a downstream facing step in a wall into a high-temperature stream. Temperature and hydroxyl radical concentration are measured downstream of the injection plane by means of ultraviolet absorption spectroscopy. The experimental results are compared with theory which is based on a finite-difference solution of boundary-layer equations. Finite-rate kinetics equations are included in the analysis. The analytic predictions are also compared with previously obtained experimental results which are based on probe measurements. Comparison is made between calculated and observed ignition distances.
    Keywords: PROPULSION SYSTEMS
    Type: Joint Fluids Engineering Conference; May 13, 1974 - May 15, 1974; Montreal; Canada
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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    Overview of NASA aeronautical propulsion research and technology program (1974)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The program discussed is aimed at improving performance within an extended operating range, reducing weight, increasing service life, achieving greater cost effectiveness, reducing noise and exhaust pollution, and improving means of energy conservation. The program places emphasis on basic research in numerous related technical disciplines, system analysis, component technology, full scale propulsion system studies, and technology demonstrations. Much attention in the discussion is given to noise and pollution minimization research.
    Keywords: PROPULSION SYSTEMS
    Type: ICAS PAPER 74-51 , International Council of the Aeronautical Sciences Congress; Aug 25, 1974 - Aug 30, 1974; Haifa; Israel
    Format: text
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    NASA TECHNICAL REPORTS
  • 7
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    Effects of forward velocity and acoustic treatment on inlet fan noise (1974)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Flyover and static noise data from several engines are presented that show inlet fan noise measured in flight can be lower than that projected from static tests for some engines. The differences between flight and static measurements appear greatest when the fan fundamental tone due to rotor-stator interaction or to the rotor-alone field is below cutoff. Data from engine and fan tests involving inlet treatment on the walls only are presented that show the attenuation from this treatment is substantially larger than expected from previous theories or flow duct experience. Data showing noise shielding effects due to the location of the engine on the airplane are also presented. These observations suggest that multiringed inlets may not be necessary to achieve the desired noise reduction in many applications.
    Keywords: PROPULSION SYSTEMS
    Type: AIAA PAPER 74-946 , Aircraft Design, Flight Test and Operations Meeting; Aug 12, 1974 - Aug 14, 1974; Los Angeles, CA
    Format: text
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    NASA TECHNICAL REPORTS
  • 8
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    Development of high temperature materials for solid propellant rocket nozzle applications (1974)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Aspects of the development and characteristics of thermal shock resistant hafnia ceramic material for use in solid propellant rocket nozzles are presented. The investigation of thermal shock resistance factors for hafnia based composites, and the preparation and analysis of a model of elastic materials containing more than one crack are reported.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-CR-138804 , QPR-12
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    FOD impact testing of composite fan blades (1974)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The results of impact tests on large, fiber composite fan blades for aircraft turbofan engine applications are discussed. Solid composite blades of two different sizes and designs were tested. Both graphite/epoxy and boron/epoxy were evaluated. In addition, a spar-shell blade design was tested that had a boron/epoxy shell bonded to a titanium spar. All blades were tested one at a time in a rotating arm rig to simulate engine operating conditions. Impacting media included small gravel, two inch diameter ice balls, gelatin and RTV foam-simulated birds, as well as starlings and pigeons. The results showed little difference in performance between the graphite and boron/epoxy blades. The results also indicate that composite blades may be able to tolerate ice ball and small bird impacts but need improvement to tolerate birds in the small duck and larger category.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-TM-X-71544 , Natl. SAMPE Symp. and Exhibition; Apr 23, 1974 - Apr 25, 1974; Buena Park, CA; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    The experimental clean combustor program: Description and status (1974)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The objectives, program plan, schedule, pollution and performance goals, program approaches to pollution reduction, and status of the project are presented. Advanced supersonic transport and combustion noise programs are also discussed. The phases of the program consist of the following: (1) screening of low pollutant combustors, (2) refinement of the best combustors, and (3) engine demonstration of the best combustors. It is stated that all combustor designs investigated appear capable of achieving the idle pollutant goals with additional development effort.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-TM-X-71547 , E-7956 , Air Transport Meeting; Apr 30, 1974 - May 02, 1974; Dallas
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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