ROTOR IMPELLER OF LP COMPRESSOR OF JET TURBINE ENGINE (VERSIONS) Russian patent published in 2015 - IPC F04D29/32 F01D5/06 

FIELD: machine building.

SUBSTANCE: 1st stage impeller of the rotor shaft of LP compressor of the jet turbine engine contains disk with hub, central hole, plate and rim, and blades that have convex-concave cross-section. Each blade has body and shank. The rim is asymmetrically connected with the blade body with creation of two flows of face and rear cone flanges that have different arms and inclined towards the vector. The summary equal-arm part of flanges width has slots, in which the blade shanks are inserted. The rear flange of the rim is amended with the ring broadening projecting beyond the blade body, and exceeding width of the face flange. In the projection to the relative axial plane perpendicular to the blade body the longitudinal axis of each slot with the impeller axis creates angle α₀ of the shank installation in range α₀ = (17÷27)°. The slots are uniformly distributed along the disk perimeter. At that chord of side edges of the body in the root zone of the blade creates with the rotor axis in projection the body installation angle α_e increasing along radial height of the blade body with gradient of the body twisting, G_b.t. = (124.0÷186.8) [degrees/m].

EFFECT: increased efficiency and margin of GDU at all operation modes of the compressor upon durability increasing of the 1st stage impeller of LP compressor without increasing of materials consumption.

11 cl, 5 dwg