VENICE SHOULDER gas turbines blowing cooling air into the trailing edge CUT SHOULDER

摘要

The invention relates to aircraft engine, in particular a high-temperature turbines of aircraft gas turbine engines. The technical result, which is aimed at achieving the utility model is to increase the efficiency and effectiveness of the cooling of the turbine blades due to the geometry of the cut, located in the area of ​​the openings for discharging the cooling medium to the outlet edge of the vane. The technical result is achieved in that a vane crown of a gas turbine with blowing cooling air into the cut off blade edges, comprises cooled blade forming interblade channels and each having a hollow quill with holes for discharging cooling medium is arranged from the trough of the pen in the trailing edge zone, this pen has a section of each blade, located in the area of ​​the openings for discharging the cooling medium to the outlet edge of the vane. The novelty of the utility model is that the interscapular channel portion from the openings for discharging the cooling medium to the trailing edge area is formed with a variable flow cross section, increasing from the beginning of the holes for discharging the cooling medium to the trailing edge of the blade is not more than 5%.