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Effect of Radial Curvature in Rockets on Film Cooling Adiabatic Effectiveness and Jet Width

[+] Author Affiliations
Jonathan F. McCall

Air Force Institute of Technology, Wright-Patterson AFB, OH

Richard D. Branam

Air Force Institute of Technology, Wright Patterson AFB, OH

Paper No. IMECE2008-69055, pp. 539-547; 9 pages
  • ASME 2008 International Mechanical Engineering Congress and Exposition
  • Volume 10: Heat Transfer, Fluid Flows, and Thermal Systems, Parts A, B, and C
  • Boston, Massachusetts, USA, October 31–November 6, 2008
  • Conference Sponsors: ASME
  • ISBN: 978-0-7918-4871-5 | eISBN: 978-0-7918-3840-2


A computational study was performed to determine the effects of radial curvature on film cooling adiabatic effectiveness. This curvature is typically encountered in modern rocket combustion sections. Jet width and spanwise-averaged adiabatic effectiveness are observed to slightly decrease as radius of curvature decreases. This decrease impacts hole spacing requirements for adequate thermal management inside rocket combustors. Compound injection aggravates the effect so that the increased adiabatic efficiency usually associated is diminished due to a cradling effect of the radial curvature. The result is an increase in adia-batic efficiency immediately downstream of the hole and a decrease after 2 hole diameters, when compared to the flat plate. Furthermore, increasing the momentum ratio past 1 diminishes the effect of radial curvature on adiabatic effectiveness. Quantified understanding of radial curvature effects allow one to use flat plate effectiveness correlations for sizing of film cooling systems in internal flow situations, like rocket combustion chambers. This research is funded and supported by AFRL Propulsion Directorate.

Topics: Cooling , Rockets



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