TURBINE BLADE Russian patent published in 2005 - IPC

FIELD: mechanical engineering; gas-turbine engines.

SUBSTANCE: proposed turbine blade of gas-turbine engine consists of air-foil portion and lock part. Air-foil portion in zone of maximum thermal stresses includes layers of material applied to main body of blade. Materials of adjacent applied layers are chosen so that linear expansion coefficient of layer of material exposed to action of higher temperature should be lower than coefficient of layer of material with lower temperature. Materials of applied layers are chosen so that in adjacent layers exposed to action of close temperatures in place of contact, modulus of elasticity of layer having larger deformation should be higher than modulus of elasticity of layer having lower deformation. Applied layers of blade have variable thickness.

EFFECT: increased thermocyclic life of blade owing to prevention of appearance of thermal stresses.

2 cl, 2 dwg