IMPINGEMENT COOLING PERFORMANCE IN GAS TURBINE AIRFOILS INCLUDING EFFECTS OF LEADING EDGE SHARPNESS

An experimental study of the heat transfer characteristics of impingement into cavities which model the cooled leading edges of gas turbine engine airfoils is presented. The study includes both two-dimensional slot jets and single lines of evenly-spaced circular jets. For broad cylindrical cavities correlations are given for the maximum heat transfer rates attainable with optimum positioning of the jet nozzle with respect to the cooled surface. For elongated narrow cavities heat transfer rates relative to these maximum values are presented for a variety of cavity shapes.

• Corporate Authors:

  American Society of Mechanical Engineers

  Two Park Avenue
  New York, NY  United States  10016-5990
• Authors:
  • METZGER, D
  • Baltzer, R
  • JENKINS, C
• Publication Date: 1972-7

Media Info

• Pagination: p. 219-225
• Serial:
  • ASME Journal of Engineering for Power
  • Volume: 94AN
  • Issue Number: 3
  • Publisher: American Society of Mechanical Engineers

Subject/Index Terms

• TRT Terms: Blades (Machinery); Design; Gas turbines; Heat transfer
• Subject Areas: Design; Marine Transportation; Vehicles and Equipment;

Filing Info

• Accession Number: 00035216
• Record Type: Publication
• Source Agency: United States Merchant Marine Academy
• Files: TRIS
• Created Date: Oct 27 1973 12:00AM