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  • 1
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    A new hue capturing technique for the quantitative interpretation of liquid crystal images used in convective heat transfer studies (1992)
    In:  Other Sources
    Details
    Publication Date: 2011-08-24
    Description: A new image processing based color capturing technique for the quantitative interpretation of liquid crystal images used in convective heat transfer studies is presented. This method is highly applicable to the surfaces exposed to convective heating in gas turbine engines. It is shown that, in the single-crystal mode, many of the colors appearing on the heat transfer surface correlate strongly with the local temperature. A very accurate quantitative approach using an experimentally determined linear hue vs temperature relation is found to be possible. The new hue-capturing process is discussed in terms of the strength of the light source illuminating the heat transfer surface, the effect of the orientation of the illuminating source with respect to the surface, crystal layer uniformity, and the repeatability of the process. The present method is more advantageous than the multiple filter method because of its ability to generate many isotherms simultaneously from a single-crystal image at a high resolution in a very time-efficient manner.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: ASME, Transactions, Journal of Turbomachinery (ISSN 0889-504X); 114; 4; p. 765-775.
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Use of a liquid-crystal and heater-element composite for quantitative, high-resolution heat-transfer coefficients on a turbine airfoil including turbulence and surface-roughness effects (1987)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Description: Local heat transfer coefficients were measured along the midchord of a three-times-size turbine vane airfoil in a static cascade operated at room temperature over a range of Reynolds numbers. The test surface consisted of a composite of commercially available materials: a Mylar sheet with a layer of cholestric liquid crystals, which change color with temperature, and a heater made of a polyester sheet coated with vapor-deposited gold, which produces uniform heat flux. After the initial selection and calibration of the composite sheet, accurate, quantitative, and continuous heat transfer coefficients were mapped over the airfoil surface. Tests were conducted at two free-stream turbulence intensities: 0.6 percent, which is typical of wind tunnels; and 10 percent, which is typical of real engine conditions. In addition to a smooth airfoil, the effects of local leading-edge sand roughness were also examined for a value greater than the critical roughness. The local heat transfer coefficients are presented for both free-stream turbulence intensities for inlet Reynolds numbers from 1.20 to 5.55 x 10 to the 5th power. Comparisons are also made with analytical values of heat transfer coefficients obtained from the STAN5 boundary layer code.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Effect of hole geometry and Electric-Discharge Machining (EDM) on airflow rates through small diameter holes in turbine blade material (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The effects of two design parameters, electrode diameter and hole angle, and two machine parameters, electrode current and current-on time, on air flow rates through small-diameter (0.257 to 0.462 mm) electric-discharge-machined holes were measured. The holes were machined individually in rows of 14 each through 1.6 mm thick IN-100 strips. The data showed linear increase in air flow rate with increases in electrode cross sectional area and current-on time and little change with changes in hole angle and electrode current. The average flow-rate deviation (from the mean flow rate for a given row) decreased linearly with electrode diameter and increased with hole angle. Burn time and finished hole diameter were also measured.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TP-1716 , E-417
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Heater Composite Measures Heat Transfer (1982)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Composite consisting of commercially available elements has been developed to measure heat transfer. Composite provides a simple, convenient, low-cost device for use in heat-transfer work for rapid evaluation of thermal performance of both flat and simply curved objects. Device utilizes available off-the-shelf materials and provides a convenient method, with good resolution of local temperatures and heat transfer, with measurement accuracy at near-normal room conditions.
    Keywords: MECHANICS
    Type: LEW-13731 , NASA Tech Briefs (ISSN 0145-319X); 6; 2; P. 192
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    Local heat-transfer measurements on a large, scale-model turbine blade airfoil using a composite of a heater element and liquid crystals (1985)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Local heat transfer coefficients were experimentally mapped along the midchord of a five-time-size turbine blade airfoil in a static cascade operated at room temperature over a range of Reynolds numbers. The test surface consisted of a composite of commercially available materials: a mylar sheet with a layer of cholesteric liquid crystals, that change color with temperature, and a heater sheet made of a carbon-impregnated paper, that produces uniform heat flux. After the initial selection and calibration of the composite sheet, accurate, quantitative, and continuous heat transfer coefficients were mapped over the airfoil surface. The local heat transfer coefficients are presented for Reynolds numbers from 2.8 x 10 to the 5th power to 7.6 x 10 to the 5th power. Comparisons are made with analytical values of heat transfer coefficients obtained from the STAN5 boundary layer code. Also, a leading edge separation bubble was revealed by thermal and flow visualization.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-TM-86900 , E-2347 , NAS 1.15:86900
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Computer program for obtaining thermodynamic and transport properties of air and products of combustion of ASTM-A-1 fuel and air (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A computer program for determining desired thermodynamic and transport property values by means of a three-dimensional (pressure, fuel-air ratio, and either enthalpy or temperature) interpolation routine was developed. The program calculates temperature (or enthalpy), molecular weight, viscosity, specific heat at constant pressure, thermal conductivity, isentropic exponent (equal to the specific heat ratio at conditions where gases do not react), Prandtl number, and entropy for air and a combustion gas mixture of ASTM-A-1 fuel and air over fuel-air ratios from zero to stoichiometric, pressures from 1 to 40 atm, and temperatures from 250 to 2800 K.
    Keywords: PROPELLANTS AND FUELS
    Type: NASA-TP-1160 , E-9371
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Radiation heat transfer characteristics of turbine vane airfoils in a water-cooled cascade (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Radiation heat transfer characteristics of turbine vane airfoils in water-cooled cascade
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-TM-X-2203 , E-5862
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Aerodynamic investigation of four-vane cascade designed for turbine cooling studies Technical memorandum (1970)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Aerodynamic characteristics of annular sector, four vane cascade made for cooled turbine thermodynamic studies
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-1954 , E-5294
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    Pressure-loss and flow coefficients inside a chordwise-finned, impingement, convection, and film air-cooled turbine vane (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Total-pressure-loss coefficients, flow discharge coefficients, and friction factors were determined experimentally for the various area and geometry changes and flow passages within an air-cooled turbine vane. The results are compared with those of others obtained on similar configurations, both actual and large models, of vane passages. The supply and exit air pressures were controlled and varied. The investigation was conducted with essentially ambient-temperature air and without external flow of air over the vane.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-3028 , E-7719
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    Evaluation of a method for heat transfer measurements and thermal visualization using a composite of a heater element and liquid crystals (1981)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Commercially available elements of a composite consisting of a plastic sheet coated with liquid crystal, another sheet with a thin layer of a conducting material (gold or carbon), and copper bus bar strips were evaluated and found to provide a simple, convenient, accurate, and low-cost measuring device for use in heat transfer research. The particular feature of the composite is its ability to obtain local heat transfer coefficients and isotherm patterns that provide visual evaluation of the thermal performances of turbine blade cooling configurations. Examples of the use of the composite are presented.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: ASME PAPER 81-GT-93 , Gas Turbine Conference and Products Show; Mar 09, 1981 - Mar 12, 1981; Houston, TX
    Format: text
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    NASA TECHNICAL REPORTS
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