GAS TURBINE ENGINE COMPRESSOR IMPELLER Russian patent published in 2018 - IPC F01D5/32 F04D29/34 

FIELD: motors and pumps.

SUBSTANCE: invention relates to aircraft engine technology, particularly to the aircraft gas turbine engines axial compressors. Impeller of the gas turbine engine axial compressor comprises disk with the conical outer surface, which is oriented towards the impeller input end by the smaller base, working blades with shanks placed in the grooves formed on the disc outer surface with the radial gap formation between the shank lower surface and the groove inner surface, fixing inserts located in the radial gap and formed by this gap shape from the material, which is more plastic than the material of which the blades and the disk are made, and the fixing inserts movement along the groove limiters, wherein the grooves on the disc outer surface are oriented at an acute angle to the disk longitudinal section diametral plane and at an acute angle to the impeller output end surface, the fixing insert has at least one protrusion, and the shank is located on mutually contacting surfaces at least one depression corresponding to the protrusion in the form. According to the invention, on the impeller output end side the disc grooves are made hollow, the grooves and fixing inserts end mating surfaces are made spherical, and in the disk cross section plane the inserts each protrusion surface generatrix has the form of the circle part, which is conjugated with a straight line section inclined relative to the insert plane surface and smoothly coupled to it.

EFFECT: invention allows to ensure the contact stresses uniform distribution at a level of 600–800 MPa over the blade shank and the impeller disk contact surfaces.

3 cl, 5 dwg