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. First stage of impeller vane, 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 flow confined in peripheral outline by engine housing, having power turbine, comprises stem and wing 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 of feather a value γ_ust.k.= (67.5÷75.5)°, and in peripheral section value γ_ust.p= (36.9÷44.9)°. 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)_{u p}= (144.9÷208.3) [deg/m]. Blade feather has leading and trailing edges diverging to peripheral end with chord increase gradient (G)_{y. x}= (8.4÷12.1)·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 of feather to peripheral end with gradient (G)_u.t.=(1.0÷1.44)·10^-2 [m/m].

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

25 cl, 3 dwg