Sectorized ring for use in rotor of high pressure gas turbine of turbojet of aircraft, has ventilation openings whose cross section at slits is greater than width of slits so as to have lower and upper cooling zones on sides of strips

摘要

The ring has lower sealing strips (18) whose reception slits (20) facing toward a vein are arranged in parallel around internal side faces (12) of sectors (5) and extend from a transverse upstream face to a transverse downstream face of the sectors. Ventilation openings (25) passing through the slits emerge directly in radial faces (11) of the sectors. The openings are identical and regularly distributed along the slits. A cross section of the openings at the slits is greater than width of the slits so as to have lower and upper cooling zones on sides of the strips, respectively.