IMPELLER VANE OF TURBOJET ENGINE LOW-PRESSURE COMPRESSOR ROTOR (VERSIONS) Russian patent published in 2016 - IPC F04D29/38 F01D5/14 

FIELD: engines.

SUBSTANCE: vane of the fourth stage of turbojet engine low-pressure compressor rotor containing an impeller with disc with slots, and blade rim with grating profiles of the feather with frontal line. Blade comprises stem and vane with convex-concave profile. Airfoil has angle of γ installation of profile, defined as angle between connecting inlet and outlet edge of profile of chord and front line grid of blade rim, with its projection to conditional plane perpendicular to axis of the blade in root section profile value γ_to=(49.7÷57.7)°. 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 the gradient (G)_{in n}=(152.3÷218.9) [degree/m]. Blade root has leading and trailing edges, diverging to peripheral end with the chord increase gradient (G)_{in x}=(4.3÷6.2)·10^-2 [m/m]. Blade is made with the ratio of height h of the leading edge of the feather profile to central chord L_av, separating area of working surface profile into two equal parts making h/L_av=(1.5÷2.2). Blade feather has, variable on width and height, blade thickness. Maximum thickness of blade root profile is the highest in root section and height decreasing to peripheral end with Airfoil gradient (G)_{in t}=(1.6÷2.3)10^-2 [m/m].

EFFECT: technical result consists in improvement of efficiency and wider range of modes of gas-dynamic stability of the compressor to 2,4%, longer life of blade in 2 times.

25 cl, 4 dwg