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  • Other Sources  (5)
  • Metals and Metallic Materials  (4)
  • Spacecraft Design, Testing and Performance
  • 2015-2019
  • 1955-1959
  • 1945-1949  (5)
  • 1947  (5)
  • 1
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    Unknown
    Review of an Investigation of Ceramic Coatings for Metallic Turbine Parts and Other High-temperature Applications (1947)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: No abstract available
    Keywords: Metals and Metallic Materials
    Type: NACA-TN-1186
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Unknown
    Changes Found on Run-In and Scuffed Surfaces of Steel Chrome Plate, and Cast Iron (1947)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A study was made of run-in and scuffed steel, chrome-plate, and cast-iron surfaces. X-ray and electron diffraction techniques, micro-hardness determinations, and microscopy were used. Surface changes varied and were found to include three classes: chemical reaction, hardening, and crystallite-size alteration. The principal chemical reactions were oxidation and carburization.
    Keywords: Metals and Metallic Materials
    Type: NACA-TN-1432 , AD-A801570
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    A Preliminary Study of Ram-Actuated Cooling Systems for Supersonic Aircraft (1947)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: An analysis has been made of the characteristics of several cooling cycles suitable for cockpit cooling of supersonic aircraft. All the cycles considered utilize the difference between dynamic and ambient static pressure to actuate the cooling system and require no additional power source. The results of the study indicate that as flight speeds become greater, increasingly complex systems are required to reduce the altitudes above approximately 35,000 feet, a system composed of an externally loaded expansion turbine in conjunction with a supersonic diffuser would maintain tolerable ventilating air temperature, at least up to a flight Mach number of 2. The most complex system considered,composed of compressor, intercooler, and expansion turbine with the intercooler cooling air decreased in temperature by expansion through an auxiliary turbine is capable of maintaining a ventilation air temperature less than ambient temperature up to a flight Mach number of 3.7.
    Keywords: Spacecraft Design, Testing and Performance
    Type: NACA-RM-A7C04
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Unknown
    The Crystal Structure at Room Temperature of Six Cast Heat-Resisting Alloys (1947)
    In:  CASI
    Details
    Publication Date: 2019-08-16
    Description: The crystal structures of alloys 61, X-40,X-50, 422-19, 6059, and Vitallium, derived from x-ray diffraction, are discussed. The alloys have been, or are being considered for use in gas turbine applications. The predominant phase was a solid solution of the face centered cubic type of the principal constituent elements.The lattice parameters were found to be between 3.5525 and 3.5662.
    Keywords: Metals and Metallic Materials
    Type: NACA-RM-E7D23
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Unknown
    Cyclic Engine Test of Cast Vitallium Turbine Buckets - I (1947)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: An investigation was conducted to correlate the engine service performance of cast Vitallium turbine buckets with standard laboratory metallurgical data. Data were obtained from four I-40 turbine wheels of Timken alloy with cast Vitallium buckets. In order to accelerate bucket deterioration, the turbine wheels were subjected to 20-minute cycles consisting of 5 minutes at idle and 15 minutes at rated speed. A bucket broke on the first wheel during cycle 22 after 7 hours and 20 minutes. The broken bucket was replaced and during the third cycle after the replacement a second bucket broke after a total running time of 8 hours and 12 minutes, The first bucket failure on the second wheel occurred during cycle 29 after 9 hours and 28 minutes; no further failure occurred during 66 additional cycles. Total running time on this wheel was 31 hours and 40 minutes. The third wheel was run for 229 cycles (76 hr and 20 min, total running time) without a. failure. The fourth wheel was operated for 105 cycles (35 hr, total running time) without a failure. Examination of the bro?en buckets indicated that the failures were probably due to fatigue, Massive eutectic areas that existed near the trailing edge probably contributed to the low fatigue strength.
    Keywords: Metals and Metallic Materials
    Type: NACA-RM-SE7B07 , NACA-RM-E7B07
    Format: application/pdf
    Location Call Number Expected Availability
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    NASA TECHNICAL REPORTS
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