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

FIELD: engines.

SUBSTANCE: invention relates to engine building. 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. 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 disc 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 α_k=(17÷27)°. 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 range of (G)_u.p= (159.2÷245.8) [degree/m]. Airfoil is made with input and output edges diverging to the peripheral end with a gradient of chard increasing G_u.x, equal to (1.6÷2.5)·10^-2 [m/m]. Blade profile depth is maximum in root section and height decreasing in airfoil height to peripheral end with gradient G_u.t= (1.42÷1.71)·10^-2 [m/m].

EFFECT: technical result consists in improved geometrical configuration, spatial stiffness, structural and aerodynamic parameters of second stage of gas turbine engine low-pressure compressor rotor shaft, increased service life without increase of material consumption and labour input of blade in compressor impeller.

25 cl, 4 dwg