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  • Other Sources  (7)
  • NASA Technical Reports  (7)
  • Propellants and Fuels  (5)
  • MACHINE ELEMENTS AND PROCESSES
  • 1945-1949  (6)
  • 1930-1934  (1)
  • 1925-1929
  • 1
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    Altitude Performance of AN-F-58 Fuels in British Rolls-Royce Nene Single Combustor (1949)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: An investigation was conducted with a single combustor from a British Rolls-Royce Nene turbojet engine to determine the altitude performance characteristics of AN-F-58 fuels. Three fuel blends conforming to AN-F-58 specifications were prepared in order to determine the influence of fuel boiling temperatures and aromatic content on combustion efficiencies and altitude operational limits. The performance of the three AN-F-58 fuels was compared in the range of altitudes from sea level to 65,000 feet, engine speeds from 40- to 100- percent normal rated, and flight Mach numbers of 0.0 and 0.6. Similar information was obtained for AN-F-32 fuel at a flight Mach number of 0.0
    Keywords: Propellants and Fuels
    Type: NACA-RM-E9D08 , Rept-1114
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Rocket Power Plants Based on Nitric Acid and their Specific Propulsive Weights (1947)
    In:  CASI
    Details
    Publication Date: 2019-08-17
    Description: Two fields are reserved for the application of rocket power plants. The first field is determined by the fact that the rocket power plant is the only type of power plant that can produce thrust without dependence upon environment. For this field,the rocket is therefore the only possible power plant and the limit of what may be done is determined by the status of the technical development of these power plants at the given moment. The second field is that in which the rocket power plant proves itself the most suitable as a high-power drive in free competition with other types of power plants. The exposition will be devoted to the demarcation of this field and its division among the various types of rocket power plants.
    Keywords: Propellants and Fuels
    Type: NACA-TM-1145 , R-Antriebe, Schriften der Deutsche Akademie der Luftfahrtforschung; No. 1071; Nr. 82; 91-126
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Knock-Limited Performance of Triptane and Xylidines Blended with 28-R Aviation Fuel at High Compression Ratios and Maximum-Economy Spark Setting (1946)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: An investigation was conducted to evaluate the possibilities of utilizing the high-performance characteristics of triptane and xylidines blended with 28-R fuel in order to increase fuel economy by the use of high compression ratios and maximum-economy spark setting. Full-scale single-cylinder knock tests were run with 20 deg B.T.C. and maximum-economy spark settings at compression ratios of 6.9, 8.0, and 10.0, and with two inlet-air temperatures. The fuels tested consisted of triptane, four triptane and one xylidines blend with 28-R, and 28-R fuel alone. Indicated specific fuel consumption at lean mixtures was decreased approximately 17 percent at a compression ratio of 10.0 and maximum-economy spark setting, as compared to that obtained with a compression ratio of 6.9 and normal spark setting. When compression ratio was increased from 6.9 to 10.0 at an inlet-air temperature of 150 F, normal spark setting, and a fuel-air ratio of 0.065, 55-percent triptane was required with 28-R fuel to maintain the knock-limited brake power level obtained with 28-R fuel at a compression ratio of 6.9. Brake specific fuel consumption was decreased 17.5 percent at a compression ratio of 10.0 relative to that obtained at a compression ratio of 6.9. Approximately similar results were noted at an inlet-air temperature of 250 F. For concentrations up through at least 20 percent, triptane can be more efficiently used at normal than at maximum-economy spark setting to maintain a constant knock-limited power output over the range of compression ratios tested.
    Keywords: Propellants and Fuels
    Type: NACA-RM-E6J07
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    NASA TECHNICAL REPORTS
  • 4
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    Effect of Water-Alcohol Injection and Maximum Economy Spark Advance on Knock-Limited Performance and Fuel Economy of a Large Air-Cooled Cylinder (1945)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An investigation was conducted to determine the effect of a coolant solution of 25 percent ethyl alcohol, 25 percent methyl alcohol, and 50 percent water by volume and maximum-economy spark advance on knock-limited performance and fuel economy of a large air-cooled cylinder. The knock-limited performance of the cylinder at engine speeds of 2100 and 2500 rpm was determined for coolant-fuel ratios of 0.0, 0.2, and 0.4. The effect of water-alcohol injection on fuel economy was determined in constant charge-air flow tests. The tests were conducted at a spark advance of 20 deg B.T.C. and maximum-economy spark advance.
    Keywords: Propellants and Fuels
    Type: NACA-WR-E-264 , NACA-MR-E5H12
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    The Effect of Compression Ratio on Knock Limits of High-Performance Fuels in a CFR Engine II : Blends of 2,2,3-Trimethylpentane with 28-R (1945)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The knock-limited performance of blends of 0,50; and 100 percent by volume of 2,2,3-trimethylpentane in 28-R fuel determined with a modified F-4 engine at three sets of conditions varying from severe to mild at each of three compression ratios (6.0, 8.0, and 10.0). A comparison of the knock-limited performance of 2,2,3-trimethylpentane with that of triptane (2,2,3-trimethylbutane) is included. The knock-Limited performance of 2,2,3-trimethylpontane was usually more sensitive to either compression ratio or inlet-air temperature than 28-R fuel, but the ratio of the knock-limited indicated mean effective pressure of a given blend containing 2,2,3-trimethypentane and 28-R to the indicated mean effective pressure of 28-R alone was not greatly affected by compression ratio if the engine operating conditions were mild. Although 2,2,3-trimethylpentane in general had a lower knock-limited performance than triptane, the characteristics of the two fuels were somewhat similar.
    Keywords: Propellants and Fuels
    Type: NACA-WR-E-249 , NACA-MR-E5A10
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    NASA TECHNICAL REPORTS
  • 6
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    CONSIDERATIONS IN DESIGN OF CALORIMETERS FOR THE PROJECT FIRE SUPERORBITAL RE-ENTRY TEST VEHICLE (1945)
    In:  Other Sources
    Details
    Publication Date: 2019-05-10
    Description: Design of calorimeters to obtain flight data at lunar reentry velocity and equations to convert telemetered temperature responses into heat flux valves
    Keywords: MACHINE ELEMENTS AND PROCESSES
    Type: SAE PAPER 750L
    Format: text
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  • 7
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    Evaluation of drilled-ball bearings at DN values to three million. 1: Variable oil flow tests (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Two 125-mm-bore solid ball bearings and two similar drilled ball bearings were operated at speeds up to 24,000 rpm (3.0 million DN) with a 13,000 newton (3000 lb) thrust load. The oil flow rate was varied from 0.045 to 0.121 kilograms per second (6 to 16 lb/min). The solid ball bearings operated satisfactorily over the entire range of conditions. The drilled ball bearing experienced cage rub with marginal lubrication at 0.045 kilograms per second (6 lb/min). The drilled ball bearing generally ran cooler than the solid ball bearings.
    Keywords: MACHINE ELEMENTS AND PROCESSES
    Type: NASA-CR-2004 , PWA-4235
    Format: application/pdf
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