ROTOR BLADE FOR GAS-TURBINE ENGINE (VARIANTS) Russian patent published in 2017 - IPC F01D5/30 

FIELD: engines and pumps.

SUBSTANCE: rotor blade comprises an aerofoil stretching, a root that is integral connected to an aerofoil stretching, and a locking piece that is integral connected to a root and that is installed in the gas-turbine engine rotor hub slot. A locking piece comprises a dovetail, a journal between a root and a dovetail, and a groove that is formed in a journal. A dovetail comprises a contact area that is configured to be in contact with the slot surface for the rotor blade holding in the hub. A groove provides a reverse of voltage direction in the rotor blade and places at a distance from the contact area. A groove begins from the rotor following edge side and extends to the rotor leading edge side and has a following edge side initial non-zero depth and gradually tapers to the point of the zero depth towards the leading edge. In other option of rotor blade accomplishment, the groove is defined by the cylinder surface. The cylinder crosses the journal at the initial non-zero depth and has an axial axis at an nonzero angle in regard to the dovetail length direction. Along with this, the cylinder radius is greater than the initial non-zero depth.

EFFECT: group of inventions permits to enhance a gas-turbine engine rotor blade reliability by virtue of the decrease of the crack formation and deterioration on the surface of the blade locking piece.

8 cl, 6 dwg