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

FIELD: engines and pumps.

SUBSTANCE: blade of grooved disc of rotor of LP compressor of gas turbine engine (GTE) including flow part confined in peripheral outline by engine housing comprises shank and foil. Said blade can be fitted in whatever groove of the first stage impeller disc. Blade shank has a longitudinal axis aligned or parallel to the geometrical axis of the disk groove forming together with the rotor rotation axis in projection to arbitrary axial a plane perpendicular to airfoil radial axis; the shank angle providing the installation angle of the foil profile in the blade root section within the range αk=(17÷27)°. Airfoil is made with spinning relative to the axis of the airfoil, which provides increase of the installation angle of the airfoil profile in height of the blade with a radial distance from the rotor rotation axis with gradient (G)_u.p., defined in the range G_u.p.=(124.0÷186.8) [degree/m]. Airfoil is made with input and output edges diverging to the peripheral end with a gradient of chard increasing G_u.h., equal to (7.2÷10.7)·10^-2 [m/m]. Airfoil profile depth is maximum in root section and decreases along the airfoil height towards peripheral end with gradient (G)_u.t.=(1.25÷1.53)·10^-2 [m/m].

EFFECT: technical result achieved by the group of inventions consists in improved geometrical configuration, spatial stiffness, structural and aerodynamic parameters of the first stage of gas turbine engine low-pressure compressor rotor shaft, increased service life without increase of material consumption and labor input when mounting the blade into compressor impeller.

25 cl, 4 dwg