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  • FLUID MECHANICS AND HEAT TRANSFER  (7)
  • 2015-2019
  • 1985-1989  (3)
  • 1975-1979  (4)
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  • 2015-2019
  • 1985-1989  (3)
  • 1975-1979  (4)
  • 1980-1984  (4)
Year
  • 1
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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
  • 2
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    Streakline flow visualization of discrete-hole film cooling with normal, slanted, and compound angle injection (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Film injection from discrete holes in a three-row, staggered array with five-diameter spacing was studied for three hole angles: (1) normal, (2) slanted 30 deg to the surface in the direction of the main stream, and (3) slanted 30 deg to the surface and 45 deg laterally to the main stream. The ratio of the boundary layer thickness-to-hole diameter and Reynolds number were typical of gas-turbine film-cooling applications. Detailed streaklines showing the turbulent motion of the injected air were obtained by photographing very small neutrally buoyant, helium-filled soap bubbles which follow the flow field.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-TN-D-8248 , E-8418
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Streakline flow visualization of discrete hole film cooling with holes inclined 30 deg to surface (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Film injection from three rows of discrete holes angled 30 deg to the surface in line with mainstream flow and spaced 5 diameters apart in a staggered array was visualized by using helium bubbles as tracer particles. Both the main stream and the film injectant were ambient air. Detailed streaklines showing the turbulent motion of the film mixing with the main stream were obtained by photographing small, neutrally buoyant helium-filled soap bubbles which followed the flow field. The ratio of boundary layer thickness to hole diameter and the Reynolds number were typical of gas turbine film cooling applications. The results showed the behavior of the film and its interaction with the main stream for a range of blowing rates and two initial boundary layer thicknesses.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-TN-D-8175 , E-8570
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Turbine vane coolant flow variations and calculated effects on metal temperatures (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Seventy-two air-cooled turbine vanes were tested to determine coolant flow variations among the vanes. Calculations were made to estimate the effect of measured coolant flow variations on local vane metal temperatures. The calculations were based on the following assumed operating conditions: turbine inlet temperature, 1700 K (2600 F); turbine inlet pressure, 31 N/sq cm (45 psia); coolant inlet temperature, 811 K (1000 F); and total coolant to gas flow ratio, 0.065. Variations of total coolant flow were not large (about 10 percent from the arithmetic mean) for all 72 vanes, but variations in local coolant flows were large. The local coolant flow variations ranged from 8 to 75 percent, and calculated metal temperature variations ranged from 8 to 60 K (15 to 180 F).
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-TM-X-3249 , E-8254
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    High-resolution liquid-crystal heat-transfer measurements on the endwall of a turbine passage with variations in Reynolds number (1988)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Local heat-transfer coefficients were experimentally mapped on the end-wall surface of a three-times turbine vane passage in a static, single-row cascade operated with room-temperature inlet air over a range of Reynolds numbers. The test surface was a composite of commercially available materials: a Mylar sheet with a layer of cholesteric 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 end-wall surface. The local heat-transfer coefficients (expressed as nondimensional Stanton number) are presented for inlet Reynolds numbers (based on vane axial chord) from 0.83 x 10(5) to 3.97 x 10(5).
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: ASME 1988 National Heat Transfer Conference; Jul 24, 1988 - Jul 27, 1988; Houston, TX; United States
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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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:  Other Sources
    Details
    Publication Date: 2019-07-12
    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 STANS boundary layer code. Also, a leading edge separation bubble was revealed by thermal and flow visualization.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: ASME PAPER 85-GT-59 , ASME, Transactions, Journal of Engineering for Gas Turbines and Power (ISSN 0022-0825); 107; 953-960
    Format: text
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    NASA TECHNICAL REPORTS
  • 7
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    Streakline flow visualization study of a horseshoe vortex in a large-scale, two-dimensional turbine stator cascade (1979)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Neutrally bouyant helium-filled bubbles were observed as they followed the streamlines in a horseshoe vortex system around the vane leading edge in a large scale, two dimensional, turbine stator cascade. Inlet Reynolds number, based on true chord, ranged between 100,000 to 300,000. Bubbles were introduced into the endwall boundary layer through a slot upstream of the vane leading edge. The paths of the bubbles were recorded photographically as streaklines on 16 mm movie film. Individual frames from the film were selected, and overlayed to show the details of the horseshoe vortex around the leading edge. The transport of the vortex across the passage near the leading edge is clearly seen when compared to the streaks formed by bubbles carried in the main stream. Limiting streamlines on the endwall surface were traced by the flow of oil drops.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-TM-79274 , E-201 , Intern. Gas Turbine Conf. and Products Show; Mar 09, 1980 - Mar 13, 1980; New Orleans, LA; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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