ROTOR DISK OF GAS-TURBINE ENGINE (VERSIONS) Russian patent published in 2006 - IPC F04D29/26 

FIELD: mechanical engineering; gas-turbine engines.

SUBSTANCE: proposed rotor disk of gas-turbine engine contains row of ring hubs surrounding central line. Each hub is connected with disk rim by bridge. Great number of dovetail slots spaced circumference pass between posts of disk in axial direction from front end to rear end of disk rim and in radial direction, inwards from outer surface of disk rim. To prevent breaking, ring slots pass over circumference in radial direction through rim in dovetail slots between each two adjacent bridges. In typical design version, dovetail slots are made arc-shaped. Overhand projecting forward in axial direction is arranged radially outwards on each of disk posts, and bevel is found on part of overhand of each of disk post radially to outer angle. Great number of holes of posts pass in axial direction back to rim, each hole in post passes in axial direction back into corresponding post of disk.

EFFECT: possibility of making fan disk unit for smaller radius hub which includes arc-shaped root and dovetail slot to provide adequate area of support and disk loading paths.

22 cl, 27 dwg