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  • AIRCRAFT PROPULSION AND POWER  (1)
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    Heat-Transfer Characteristics of Partially Film Cooled Plug Nozzle on a J-85 Afterburning Turbojet Engine (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Plug nozzle film cooling data were obtained downstream of a slot located at 42 percent of the total plug length on a J-85 engine. Film cooling reduced the aft end wall temperature as much as 150 K, reduced total pressure loss in the upstream convection cooling passages by 50 percent, and reduced estimated compressor bleed flow requirement by 14 percent compared to an all convectively cooled nozzle. Shock waves along the plug surface strongly influenced temperature distributions on both convection and film cooled portions. The effect was most severe at nozzle pressure ratios below 10 where adverse pressure gradients were most severe.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-X-3362 , E-8553
    Format: application/pdf
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