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

FIELD: engines and pumps.

SUBSTANCE: blade of grooved disc of low pressure compressor (LPC) rotor impeller in gas turbine engine (GTE) including flow section confined in peripheral outline of engine housing comprises foil and root. Blade is intended for installation in any of the fourth stage impeller disc grooves. Blade root has longitudinal axis aligned or parallel to the geometrical axis of the disk groove and forming together with rotor rotation axis in projection on arbitrary axial plane, perpendicular to blade foil radial axis, root installation angle providing installation angle for feather in blade root section in the range of α_k=19.7÷32.3°. Blade foil is twisted relative to foil axis, which provides increase of installation angle of foil profile in blade height with radial distancing from the rotor rotation axis with gradient G_u.p.,, defined in the range of G_u.p.=151.7÷274.0 [degree/m]. Blade foil has inlet and outlet edges diverging to peripheral end with chord increase gradient G_y.x., making (2.2÷3.2)·10^-2 [m/m]. Blade profile depth is maximum in root section and decreasing in foil height to peripheral end with gradient G_u.t.=(1.48÷1.76)·10^-2 [m/m].

EFFECT: technical result achieved by group of inventions consists in improved geometrical configuration, spatial stiffness, structural and aerodynamic parameters of the blade of GTE LPC fourth stage rotor impeller, increased service life without increasing material consumption and labor input when installing blade in compressor impeller.

23 cl, 4 dwg