IMPELLER VANE OF TURBOJET ENGINE LOW-PRESSURE COMPRESSOR ROTOR (VERSIONS) Russian patent published in 2016 - IPC F04D29/38 F01D5/14 

FIELD: engines.

SUBSTANCE: invention relates to engine building. First stage impeller vane of low-pressure compressor rotor of jet turbine engine (JTE) includes impeller with disc with slots, and blade rim with grating profiles of vane with frontal line. Blade comprises stem and vane with convex-concave profile. Airfoil has angle of γ installation of profile, defined as angle between connecting inlet and outlet edge of profile of chord and front line grid of blade rim, having in its projection to conditional plane perpendicular to axis of blade, in root section profile value γ_k=(69.7÷77.7)°. Blade has, variable on height of blade, angle γ of installation of root profile relative to front line of grid profiles of blade rim, decreasing with radial distance from rotor axis with gradient (G)_u.p=(157.1÷225.9) [deg/m]. Blade root has leading and trailing edges, diverging to peripheral end with chord increase gradient (G)_y.x= (9.3÷13.3)·10^-2 [m/m]. Airfoil has variable width and height of blade thickness. Maximum thickness of airfoil profile is highest in root section and decreases on height to peripheral end with gradient (G)_u.t= (1.3÷2.1)·10^-2 [m/m].

EFFECT: technical result consists in improved geometrical configuration, spatial stiffness, structural and aerodynamic parameters of first stage of turbojet low-pressure compressor rotor shaft, as well as high efficiency and wider range of modes under compressor blade.

25 cl, 4 dwg