GAS TURBINE ENGINE LOW PRESSURE COMPRESSOR ROTOR IMPELLER (VERSIONS) Russian patent published in 2016 - IPC F04D29/32 F01D5/06 

FIELD: engines and pumps.

SUBSTANCE: invention relates to engine building. LPC GTE third stage rotor shaft impeller comprises disc hub with central hole, web and rim, as well as blades each having tail and wing with profile formed by concave pressure side and convex back. Disc rim is connected with web to make different-arm circular conical inclined flanges. Disc radius R_d from axis to rim outer surface in web middle plane is (0.59÷0.84) from radius R_p.p. of flow part peripheral contour in said plane. Disc rim is equipped with set of blades fixation grooves uniformly distributed along disc perimeter. Each slot longitudinal axis with rotor shaft axis in projection on arbitrary axial plane makes, normal to blade root radial axis, angle of α blade root installation defined in range of values α=(17÷25)°. Blade has, variable by blade height, angle of root profile installation relative to blade rim grid profile front line, decreasing with radial distance from rotor axis with gradient G_u.p=(208.7÷300.0) [deg/m]. Besides, blade root is made with thickness variable along blade width and height. Maximum thickness of blade feather profile is highest in root section and height decreasing by blade root height to peripheral end with gradient of G_u.t.=(2.17÷3.12)∙10^-2 [m/m].

EFFECT: invention allows increasing efficiency and improve gas-dynamic stability margin at all compressor operating modes while increasing LPC rotor impeller service life without increase of material consumption.

19 cl, 6 dwg