TURBINE BLADE Russian patent published in 2009 - IPC F01D5/18 

FIELD: engines and pumps.

SUBSTANCE: turbine blade with inner cooled space features ellipsoidal radial channels arranged in the blade surface face and blade pressure surface, the ellipse larger axis being arranged parallel to tangent line running to the blade profile generating line at the point closed to the above axis. The said ellipsoidal radial channels communicate with the blade inner and outer spaces via multiple holes arranged so as to form a circular air vortex inside the above channel and a protecting film of cooling air along the blade surface face and blade pressure surface. The radial channel cross section ellipse larger axis-to-smaller axis ratio makes 1.1 to 3. The thickness of a section of the walls between ellipsoidal radial channels is at minimum to reduce the blade fin weight and the load onto the working blade created by centrifugal forces that also adds to the blade reliability. Note here that the inner space through area is also increased.

EFFECT: lower cooling air drag in ellipsoidal channels.

2 dwg