TURBOJET LOW-PRESSURE COMPRESSOR ROTOR IMPELLER BLADE Russian patent published in 2015 - IPC F04D29/38 F01D5/14 

FIELD: engines and pumps.

SUBSTANCE: claimed blade of low-pressure compressor impeller disc of turbojet with flow channel confined in peripheral outline by engine housing comprises root and butt. Said blade can be fitted in whatever groove of the second stage impeller disc. Blade butt has lengthwise axis aligned or parallel with the disc groove geometrical axis and makes with rotor axis in projection on arbitrary axial plane perpendicular to the blade root radial axis the blade pitch angle α₀ that equals α₀ = (20.44-29.8)°. Blade root features axis twist increasing at radial spacing from the rotor shaft axis with the root twist gradient G_r.t. defined in projection on axial plate to make G_r.t. = (169.54-248.4) [degree/m]. Blade root has side edges diverging to peripheral end with the chord increase gradient G_c.i. making (5.84-8.4)·10^-2 [m/m].

EFFECT: improved geometrical configuration, spatial stiffness, structural and aerodynamic parameters, higher efficiency and expanded range of the compressor gas-dynamic stability, longer life of the blade.

5 cl, 4 dwg