GAS TURBINE WITH AXIAL HOT AIR FLOW, AND AXIAL COMPRESSOR Russian patent published in 2015 - IPC F01D5/12 F01D11/00 

FIELD: machine building.

SUBSTANCE: gas turbine with axial flow contains rotor blades, guide vanes and rotating element. The rotor blades are secured on the rotor by means of the fish-bone shanks installed in the turned axial rotor channels. The blade bases create a heat protecting screens of the rotor shafts and have cavities connected with each other and with cooling air source. Between the adjacent bases of the adjacent rotor blades in direction along the circumference there is a clearance connected with cavities and passing between the bases transversely to the direction along circumference at each side of the separating plane passing through the clearance centre. The clearance is sealed at side of the gas flow by the plate sealing straps. The longitudinal end faces of the heads are located in opposite grooves of the side surfaces of bases or heat protecting screens looking towards the separating plane. The first sealing strap is installed at edges of the side surfaces at side of the gas flow passing in axial direction of the rotor shaft. Additional sealing strap is installed at the end face of the adjacent bases at edges of the side surfaces of the clearance passing in radial direction of the rotor shaft. The rotating element ensures axial locking of the rotor blade shank on the rotor, at that in the locked position it covers by the drive handle the radially opened ends of the grooves, in which the additional strap is inserted. The other invention of the group relates to the axial compressor comprising the said rotor blades, guide vanes and rotating element.

EFFECT: group of inventions improves efficiency of sealing of the clearances between blades.

7 cl, 4 dwg