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: invention relates to engine building. Third stage impeller blade with disc with slots and blade ring with frontal line grid wing profiles, in rotor of a low-pressure compressor of a gas turbine engine (GTE), comprising flow part confined in peripheral outline of engine housing with power turbine, comprises stem and wing with convex-concave profile. Blade feather is made with helical twisting relative to axis of feather, creating variable height blade angle of γ_ust of installation of root profile defined as angle between common tangent, connecting leading and trailing edges to form a chord profile, and front line grid of profiles in flat scanning of cylindrical section of blade rim with root section of feather value of γ_ust.k = (64.1÷72.1)°, and in peripheral section of value of γ_ust.p. = (17.9÷25.9)°. Blade has variable height blade angle γ of installation of root profile relative to front line grid profiles of blade rim, decreasing with radial distance from rotor axis with gradient G_u.p. = (208.7÷300.0) [deg/m]. Blade root has leading and trailing edges diverging to peripheral end with chord increase gradient G_y.h. = (7.9÷11.4)·10^-2 [m/m]. Blade feather has, variable on width and height, blade thickness. Maximum thickness of blade root profile is greatest in root section and decreasing on height to peripheral end with gradient G_u.t. = (2.17÷3.12)·10^-2 [m/m]. Widening range of modes of gas-dynamic stability of compressor by 2.2 % with prolonging life of blade by 2 times.

EFFECT: higher efficiency and wider range of modes of gas-dynamic stability of compressor.

25 cl, 3 dwg