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  • 1
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    Instrumentation design study for testing a hypersonic ramjet engine on the x-15 a-2. volume 3- conceptual design of measurement systems (1965)
    In:  CASI
    Details
    Publication Date: 2019-05-23
    Description: Instrumentation for testing hypersonic ramjet engine on X-15A-2 aircraft
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: NASA-CR-62148
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Plastic bags in evacuated chamber make lightweight gas sampling system (1965)
    In:  CASI
    Details
    Publication Date: 2019-05-23
    Description: Portable, lightweight system collects the exhaust gas of an aircraft during flight for use in analyzing combustion efficiency. The system uses an evacuated chamber and plastic bags.
    Keywords: ELECTRONIC COMPONENTS AND CIRCUITS
    Type: FRC-31
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    1700 deg C optical temperature sensor (1986)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A new gas temperature sensor was developed that shows promise of sufficient ruggedness to be useful as a gas turbine temperature sensor. The sensor is in the form of a single-crystal aluminum oxide ceramic, ground to a cone shape and given an emissive coating. A lens and an optical fiber conduct the thermally emitted light to a remote and near-infrared photodetector assembly. Being optically coupled and passive, the sensor is highly immune to all types of electrical interference. Candidate sensors were analyzed for optical sensor performance, heat transfer characteristics, stress from gas loading. This led to the selection of the conical shape as the most promising for the gas turbine environment. One uncoated and two coated sensing elements were prepared for testing. Testing was conducted to an indicated 1750 C in a propane-air flame. Comparison with the referee optical pyrometer shows an accuracy of + or - 25 C at 1700 C for this initial development. One hundred cycles from room temperature to 1700 C left the sapphire cone intact, but some loss of the platinum, 6% rhodium coating was observed. Several areas for improving the overall performance and durability are identified.
    Keywords: OPTICS
    Type: NASA-CR-175108 , NAS 1.26:175108 , R86AEB267
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Development of efflux measuring device for performance evaluation of potassium vapor turbine (1965)
    In:  CASI
    Details
    Publication Date: 2019-05-29
    Description: Vapor pressure and flow rate measuring apparatus for potassium vapor turbine
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    Advanced smoke meter development survey and analysis (1984)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Ideal smoke meter characteristics are determined to provide a basis for evaluation of candidate systems. Five promising techniques are analyzed in detail to evaluate compilance with the practical smoke meter requirements. Four of the smoke measurement concepts are optical methods: Modulated Transmission (MODTRAN), Cross Beam Absorption Counter (CBAC), Laser Induced Incandescence (LIN), and Photoacoustic Spectroscopy (PAS). A rapid response filter instrument called a Taper Element Oscillating Microbalance (TEOM) is also evaluated. For each technique, the theoretical principles are described, the expected performance is determined, and the advantages and disadvantages are discussed The expected performance is evaluated against each of the smoke meter specifications, and the key questions for further study are given. The most promising smoke meter technique analyzed was MODTRAN, which is a variation on a direct transmission measurement. The soot-laden gas is passed through a transmission cell, and the gas pressure is modulated by a speaker.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: NASA-CR-168287 , NAS 1.26:168287
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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