IMPELLER BLADE OF ROTOR OF COMPRESSOR OF LOW-PRESSURE GAS TURBINE (VERSIONS) Russian patent published in 2016 - IPC F04D29/38 F01D5/14 

FIELD: engines.

SUBSTANCE: invention relates to engine building. Impeller vane fourth stage, having a disc with slots and blade ring with frontal line of grid wing profiles, in low-pressure compressor rotor of gas turbine engine (GTE), comprising a flow part, limited on peripheral outline by engine housing, having power turbine, comprises stem and feather with convex-concave profile. Blade feather is made with helical twisting relative to axis of feather, creating variable on height of feather an angle of γ_ust of installation of feather profile, defined as angle between common tangent, connecting leading and trailing edges, forming a chord profile, and front line of profile grid in flat scanning of cylindrical section of blade rim, having in root section a value γ_ust.k = (61.3÷69.3)°, and in peripheral section a value γ_ust.p= (38.7÷46.7)°. Blade has variable on height of feather an angle γ of installation of feather profile relative to front line of profile grid of blade rim, decreasing with radial distance from rotor axis with gradient G_y.u = (217.0÷311.9) [deg/m]. Blade feather has leading and trailing edges diverging to peripheral end with chord increase gradient G_y.x = (2.9÷4.3)·10^-2 [m/m]. Blade feather has, variable on width and height, blade thickness. Maximum thickness of blade feather profile is highest in root section and decreases on height to peripheral end with gradient G_{u.t .}= (1.82÷2.62)·10^-2 [m/m].

EFFECT: technical result consists in improved geometrical configuration, spatial stiffness, structural and aerodynamic parameters of fourth stage low-pressure compressor rotor shaft gas turbine engine, as well as high efficiency and wider range of GDU modes of compressor with longer service life of blade.

25 cl, 3 dwg