Item Details

Simultaneous Film and Convection Cooling of a Plate Inserted in the Exhaust Stream of a Gas Turbine Combustor

by Cecil J. Marek and Albert J. Juhasz
Format
Book; Government Document; Online; EBook
Published
Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1973.
Language
English
Series
NASA Technical Note
Summary
Data were obtained on a parallel-flow film- and convection-cooled test section placed in the exhaust stream of a rectangular-sector combustor. The combustor was operated at atmospheric pressure and at exhaust temperatures of 589 and 1033 K (600 and 1400 F). The cooling air was at ambient pressure and temperature. Test results indicate that it is better to use combined film and convection cooling rather than either film or convection cooling alone for a fixed total coolant flow. An optimum ratio of film to convection cooling flow rates was determined for the particular geometry tested. The experimental results compared well with calculated results.
Description
iii, 34 p. : ill. ; 27 cm.
Mode of access: Internet.
Notes
  • Prepared at Lewis Research Center.
  • Cover title.
  • Bibliography: p. 34.
Series Statement
NASA technical note ; NASA TN D-7156
Logo for Copyright Not EvaluatedCopyright Not Evaluated
Technical Details

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    a| Simultaneous film and convection cooling of a plate inserted in the exhaust stream of a gas turbine combustor c| by Cecil J. Marek and Albert J. Juhasz.
    260
      
      
    a| Washington, D.C. : b| National Aeronautics and Space Administration ; a| [Springfield, Va. : b| For sale by the National Technical Information Service], c| 1973.
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    a| iii, 34 p. : b| ill. ; c| 27 cm.
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    0
      
    a| NASA technical note ; v| NASA TN D-7156
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    a| Prepared at Lewis Research Center.
    500
      
      
    a| Cover title.
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    a| Bibliography: p. 34.
    520
      
      
    a| Data were obtained on a parallel-flow film- and convection-cooled test section placed in the exhaust stream of a rectangular-sector combustor. The combustor was operated at atmospheric pressure and at exhaust temperatures of 589 and 1033 K (600 and 1400 F). The cooling air was at ambient pressure and temperature. Test results indicate that it is better to use combined film and convection cooling rather than either film or convection cooling alone for a fixed total coolant flow. An optimum ratio of film to convection cooling flow rates was determined for the particular geometry tested. The experimental results compared well with calculated results.
    538
      
      
    a| Mode of access: Internet.
    650
      
    0
    a| Combustion chambers x| Materials x| Cooling.
    650
      
    0
    a| Gas-turbines x| Combustion.
    700
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    a| Juhasz, Albert J.
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    a| United States. b| National Aeronautics and Space Administration.
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    a| Lewis Research Center.
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    b| UIU c| UIUC d| 20141113 s| google u| uiug.30112106884841 y| 1973 r| pd q| bib

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