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

FIELD: machine building.

SUBSTANCE: 4th 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 symmetrically connected with the blade body with creation of two flows of face and rear cone flanges that are equal-arm towards the vector. The rim has slots with inserted blade shanks. The disk has system of holes at equal distance from the rotor axis. 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 = (20÷32)°. 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. = (151.7÷274.0) [degrees/m].

EFFECT: increased efficiency and margin of GDU at all operation modes of the compressor upon durability increasing of the 4th stage impeller of LP compressor without increasing of materials consumption.

9 cl, 5 dwg