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. Second stage impeller vane low-pressure compressor rotor of jet turbine engine (JTE), containing impeller with disc with slots, and blade rim, having an array of root profile with front line. Blade comprises stem and wing with convex-concave profile. Blade root has angle of γ installation of profile, defined as the angle between the connecting inlet and outlet edge profile chord and front line grid of the blade rim, with its projection to conditional plane perpendicular to axis of the blade in root section profile value γ_root = (68.8÷74.8)°. Vane has variable height blade angle γ of installation of root profile relative to the front line grid profiles blade rim, decreasing with radial distance from rotor axis with the gradient (G)_{in n} = (207.3÷297.9) [degree/m]. Blade root has inlet and outlet edges diverging to peripheral end with the chord increase gradient (G)_ch.inc = (6.6÷9.5)·10^-2 [m/m]. Blade root has variable width and height of the blade thickness. Maximum thickness of blade root profile is the highest in root section and height decreasing to peripheral end with airfoil gradient (G)_e.d. = (1.54÷2.2)·10^-2 [m/m].

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

25 cl, 4 dwg