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  • Cell & Developmental Biology  (654)
  • Aircraft Propulsion and Power
  • 1960-1964  (660)
Collection
Keywords
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Years
Year
  • 1
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    Factors that Affect Operational Reliability of Turbojet Engines (1960)
    In:  CASI
    Details
    Publication Date: 2019-08-17
    Description: The problem of improving operational reliability of turbojet engines is studied. Failure statistics for this engine are presented, the theory and experimental evidence on how engine failures occur are described, and the methods available for avoiding failure in operation are discussed.
    Keywords: Aircraft Propulsion and Power
    Type: NASA-TR-R-54
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Static Thrust of an Annular Nozzle with a Concave Central Base (1960)
    In:  CASI
    Details
    Publication Date: 2019-08-17
    Description: A static test of an annular nozzle with a concave central base, producing a jet in which tangents to the jet streamlines at the exit converged toward a region on the axis of symmetry downstream of the exit, has indicated good thrust performance. A value of nozzle-flow coefficient only slightly less than unity indicates the internal loss to be small. Pressures on the concave central base are relatively large and positive, and a predictable portion of the total thrust of the jet is exerted on the central base.
    Keywords: Aircraft Propulsion and Power
    Type: NASA-TN-D-418 , L-851
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    On the Dynamic Characteristics of Free-Liquid Jets and a Partial Correlation with Orifice Geometry (1962)
    In:  CASI
    Details
    Publication Date: 2019-08-14
    Description: A technique for evaluating the dynamic characteristics of free-liquid jets on a comparative basis is presented. This method consists of determining the pressure distribution produced by the perpendicular impingement of a jet upon a flat plate and using these data for comparing and categorizing jets with unknown properties in terms of similar data produced by jets having known characteristics-i.e., with jets produced by fully developed turbulent flow, fully developed laminar flow, and a jet having a near-uniform velocity profile. The visual characteristics, as well as both the mean and the fluctuating pressure distributions, are presented for these three reference configurations and for a number of jets produced by orifices having varying length-diameter ratios, combined with varying degrees of surface roughness in the initial five diameters of straight bore.
    Keywords: Aircraft Propulsion and Power
    Type: JPL-TR-32-207
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Internal-Performance Evaluation of Two Fixed-Divergent-Shroud Ejectors (1960)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: Ejectors designed for use in a Mach 2.2 aircraft were evaluated over a range of representative primary pressure ratios and ejector corrected weight-flow ratios. Basic thrust and pumping characteristics are discussed in terms of an assumed engine operating schedule to illustrate the variation of performance with Mach number. The two designs differed about 16 percent in the shroud longitudinal spacing ratio. For corrected ejector weight-flow ratios up to 0.10, the performance of the fixed-shroud ejector designs is comparable with that of a similar continuously variable ejector except at conditions corresponding to acceleration with afterburning from Mach 0.4 to 1.2. In this region, the ejector thrust ratio decreased to a minimum of 0.96.
    Keywords: Aircraft Propulsion and Power
    Type: NASA-TM-X-257 , E-691
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Experimental Investigation of an Air-Cooled Turbine Operating in a Turbojet Engine at Turbine Inlet Temperatures up to 2500 F (1961)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: An experimental investigation was made of an air-cooled turbine at average turbine inlet temperatures up to 2500 F. A modified production-model 12-stage axial-flow-compressor turbojet engine operating in a static sea-level stand was used as the test vehicle. The modifications to the engine consisted of the substitution of special combustor and turbine assemblies and double-walled exhaust ducting for the standard parts of the engine. All of these special parts were air-cooled to withstand the high operating temperatures of the investigation. The air-cooled turbine stator and rotor blades were of the corrugated-insert type. Leading-edge tip caps were installed on the rotor blades to improve leading-edge cooling by diverting the discharge of coolant to regions of lower gas pressure toward the trailing edge of the blade tip. Caps varying in length from 0.15- to 0.55-chord length were used in an attempt to determine the optimum cap length for this blade. The engine was operated over a range of average turbine inlet temperatures from about 1600 to about 2500 F, and a range of average coolant-flow ratios of 0.012 to 0.065. Temperatures of the air-cooled turbine rotor blades were measured at all test conditions by the use of thermocouples and temperature-indicating paints. The results of the investigation indicated that this type of blade is feasible for operation in turbojet engines at the average turbine inlet temperatures and stress levels tested(maximums of 2500 F and 24,000 psi, respectively). An average one-third-span blade temperature of 1300 F could be maintained on 0.35-chord tip cap blades with an average coolant-flow ratio of about 0.022 when the average turbine inlet temperature was 2500 F and cooling-air temperature was about 260 F. All of the leading-edge tip cap lengths improved the cooling of the leading-edge region of the blades, particularly at low average coolant-flow ratios. At high gas temperatures, such parts as the turbine stator and the combustor liners are likely to be as critical as the turbine rotor blades.
    Keywords: Aircraft Propulsion and Power
    Type: NASA-TN-D-1046 , E-1163
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Internal Performance Evaluation of a Two Position Divergent Shroud Ejector (1960)
    In:  CASI
    Details
    Publication Date: 2019-08-16
    Description: A two-position divergent shroud ejector was investigated in an unheated quiescent-air facility over a range of operational variables applicable to a Mach 2.5 aircraft. The performance data are shown in terms of hypothetical engine operating conditions to illustrate variations of performance with Mach number. The overall thrust performance was reasonably good, with ejector thrust ratios ranging from 0.97 to 0.98 for all conditions except that corresponding to acceleration with afterburning through the transonic flight Mach number region from 0.9 to 1.1, where the ejector thrust ratio decreased to as low as 0.945 for an ejector corrected weight-flow ratio of 0.105.
    Keywords: Aircraft Propulsion and Power
    Type: NASA-TM-X-258 , E-753
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
    Electronic Resource
    Electronic Resource
    The importance of quantity of nerve fibers in development of nerve-induced supernumerary limbs in Triturus and enhancement of the nervous influence by tissue implantsSupported by a grant from the U. S. Public Health Service, Department of Health, Education and Welfare, RG-5820(C1). (1960)
    New York, NY : Wiley-Blackwell
    Journal of Morphology 107 (1960), S. 47-59 
    Details
    ISSN: 0362-2525
    Keywords: Life and Medical Sciences ; Cell & Developmental Biology
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Biology , Medicine
    Additional Material: 3 Tab.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1002/jmor.1051070104
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    Paper (German National Licenses)
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  • 8
    Electronic Resource
    Electronic Resource
    Masthead (1960)
    New York, NY : Wiley-Blackwell
    Journal of Morphology 106 (1960) 
    Details
    ISSN: 0362-2525
    Keywords: Life and Medical Sciences ; Cell & Developmental Biology
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Biology , Medicine
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1002/jmor.1051060101
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    Paper (German National Licenses)
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  • 9
    Electronic Resource
    Electronic Resource
    Trends in the evolution of the Actinopterygian forebrain (1962)
    New York, NY : Wiley-Blackwell
    Journal of Morphology 111 (1962), S. 69-88 
    Details
    ISSN: 0362-2525
    Keywords: Life and Medical Sciences ; Cell & Developmental Biology
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Biology , Medicine
    Additional Material: 10 Ill.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1002/jmor.1051110105
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    Paper (German National Licenses)
    Fulltext
  • 10
    Electronic Resource
    Electronic Resource
    Masthead (1962)
    New York, NY : Wiley-Blackwell
    Journal of Morphology 111 (1962) 
    Details
    ISSN: 0362-2525
    Keywords: Life and Medical Sciences ; Cell & Developmental Biology
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Biology , Medicine
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1002/jmor.1051110201
    Location Call Number Expected Availability
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    Paper (German National Licenses)
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