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  • 1
    Electronic Resource
    Electronic Resource
    Leland Ossian Howard: A Historical Review (1978)
    Palo Alto, Calif. : Annual Reviews
    Annual Review of Entomology 23 (1978), S. 1-17 
    Details
    ISSN: 0066-4170
    Source: Annual Reviews Electronic Back Volume Collection 1932-2001ff
    Topics: Biology
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1146/annurev.en.23.010178.000245
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    Paper (German National Licenses)
    Fulltext
  • 2
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    Flow visualization of film cooling with spanwise injection from a small array of holes and compound-angle injection from a large array (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Film injection from discrete holes in a smooth, flat plate was studied for two configurations: (1) spanwise injection through a four hole staggered array; and (2) compound angle injection through a 49 hole staggered array. The ratio of boundary layer thicknesses to hole diameter and the Reynolds number were typical of gas turbine film cooling applications. Streaklines showing the motion of the injected air were obtained by photographing small, neutrally buoyant, helium-filled soap bubbles that followed the flow field.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TP-1195 , E-9340
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Hydrogen film cooling of a small hydrogen-oxygen thrust chamber and its effect on erosion rates of various ablative materials (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An experimental investigation was conducted to determine what arrangement of film-coolant-injection orifices should be used to decrease the erosion rates of small, high temperature, high pressure ablative thrust chambers without incurring a large penalty in combustion performance. All of the film cooling was supplied through holes in a ring between the outer row of injector elements and the chamber wall. The best arrangement, which had twice the number of holes as there were outer row injection elements, was also the simplest. The performance penalties, presented as a reduction in characteristic exhaust velocity efficiency, were 0.8 and 2.8 percentage points for the 10 and 20 percent cooling flows, respectively, The best film-coolant injector was then used to obtain erosion rates for 19 ablative materials. The throat erosion rate was reduced by a factor of 2.5 with a 10 percent coolant flow. Only the more expensive silica phenolic materials had low enough erosion rates to be considered for use in the nozzle throat. However, some of the cheaper materials might qualify for use in other areas of small nozzles with large throat diameters where the higher erosion rates are more acceptable.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-TP-1098 , E-8909
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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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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  • 5
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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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  • 6
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    Flow visualization of discrete-hole film cooling with spanwise injection over a cylinder (1979)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Insight into the fluid mechanics encountered when film air from a single row of holes is injected over a cylinder in a mainstream at conditions simulating a film cooled, turbulent-vane leading edge was investigated. Smoke was added to the cooling air to visualize its flow path. Film was injected in the spanwise direction at angles of 30 deg and 45 deg to the surface; at angular locations of 15 deg, 30 deg, 45 deg, and 60 deg from the stagnation line; and at various blowing ratios. The observations were related to the measured heat transfer data of others. The results indicate that, in addition to the expected growth in film thickness and the greater penetration of the boundary layer with increasing blowing ration, there was an absence of spanwise spreading and only a small spanwise deflection of the injected film.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TP-1491 , E-9946
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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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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  • 8
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    Flow visualization of discrete hole film cooling for gas turbine applications (1975)
    In:  CASI
    Details
    Publication Date: 2019-07-27
    Description: Film injection from discrete holes in a three row staggered array with 5-diameter spacing is studied. The boundary layer thickness-to-hole diameter ratio and Reynolds number are typical of gas turbine film cooling applications. Two different injection locations are studied to evaluate the effect of boundary layer thickness on film penetration and mixing. Detailed streaklines showing the turbulent motion of the injected air are obtained by photographing neutrally buoyant helium filled soap bubbles which follow the flow field. The bubble streaklines passing downstream injection locations are clearly identifiable and can be traced back to their origin. Visualization of surface temperature patterns obtained from infrared photographs of a similar film cooled surface are also included.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-X-71766 , E-8418
    Format: application/pdf
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  • 9
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    Flow visualization of discrete hole film cooling for gas turbine applications (1975)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Film injection from discrete holes in a three row staggered array with 5-diameter spacing is studied for three different hole angles: (1) normal, (2) slanted 30 deg to the surface in the direction of the mainstream, and (3) slanted 30 deg to the surface and 45 deg laterally to the mainstream. The boundary layer thickness-to-hole diameter ratio and Reynolds number are typical of gas turbine film cooling applications. Two different injection locations are studied to evaluate the effect of boundary layer thickness on film penetration and mixing. Detailed streaklines showing the turbulent motion of the injected air are obtained by photographing very small neutrally buoyant helium filled 'soap' bubbles which follow the flow field. Unlike smoke, which diffuses rapidly in the high turbulent mixing region associated with discrete hole blowing, the bubble streaklines passing downstream injection locations are clearly identifiable and can be traced back to their origin. Visualization of surface temperature patterns obtained from infrared photographs of a similar film cooled surface are also included.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: ASME PAPER 75-WA/HT-12 , Winter Annual Meeting; Nov 30, 1975 - Dec 04, 1975; Houston, TX
    Format: text
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    NASA TECHNICAL REPORTS
  • 10
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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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