ROTOR BLADE OF GAS TURBINE, GAS TURBINE ROTOR AND WAY OF ROTOR ASSEMBLY Russian patent published in 2017 - IPC F01D11/00 F01D5/14 

FIELD: mechanical engineering.

SUBSTANCE: rotor blade of a gas turbine, comprising a root portion, a platform, and part of the fountain. The platform contains the input and output sides, the sides extending from the inlet to the outlet side, and an axial and a radial groove in each side of the platform. The radial groove has a first end, directed away from the axial groove, and a second end, directed to the axial groove. A second end is placed apart from the axial grooves so that between the second end of the radial grooves and the axial groove, the portion was formed, which does not contain a groove. Axial and radial grooves are arranged to overlap in the axial direction. The area has no groove in the radial direction between the size of the axial and radial groove, and the groove is in the line of sight in the axial direction. Another group of the invention relates to a rotor of a gas turbine, which comprises mentioned above blades, and axial and radial seals extending between adjacent rotor blades and held respectively axial and radial grooves on the sides of adjacent blade platforms. When the rotor is being assembled, at least two rotor blades are set above the disk. Axial seal strip is inserted through the open end of the groove further until it completely or to a greater extent is inside axial grooves. The radial sealing strip is inserted into a radial groove through the open end and a locking plate is positioned across the open end to prevent the escape of the sealing strip.

EFFECT: reduction of total leakage between the blades of the gas turbine under the action of centrifugal force when the rotor rotates.

12 cl, 2 dwg