GAS TURBINE ENGINE HIGH-PRESSURE TURBINE, RING FLANGE, SECTOR OF GUIDE VANES AND AIRCRAFT ENGINE INCLUDING HIGH-PRESSURE TURBINE Russian patent published in 2014 - IPC F01D9/04 

FIELD: engines and pumps.

SUBSTANCE: high-pressure turbine comprises assembly of guide vanes including stationary flow-levelling vanes and rotor vanes. Guide vane outer edge rests on turbine outer casing in axial direction. Guide vane inner edge slides axially in contact with inner casing outline that allows free displacement of said edge in engine axis to constrict axial displacement owing to axial support by vane outer edge. Every outer edge comprises ledges extending in direction of inner casing outline and shaped to cramp. One set of ledges is directed forward in turbine axis. Said cramps are connected in the pair of flanges. Part of ledges of front guide vanes and front flanges are arranged to make the passage for air feed to said assembly of guide vanes. Other inventions of the set relate to the sector of said guide vane assembly, ring flange connected with one of sets of said cramps, and to aircraft engine with described high-pressure turbine.

EFFECT: compensation for difference in axial expansion of outer and inner casings.

14 cl, 7 dwg