TURBOJET ENGINE LOW-PRESSURE COMPRESSOR THIRD STAGE ROTOR IMPELLER (VERSIONS) Russian patent published in 2016 - IPC F04D29/32 B01J3/00 F01D5/06 

FIELD: engines and pumps.

SUBSTANCE: invention relates to engine building. Jet engine low-pressure compressor (JTE LPC) rotor shaft third stage impeller includes disc, including 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 circular conical inclined flanges. Disc body is made with variable in height section conically narrowing from the hub to the rim. Hub is made symmetrically developed relative to web average conditional plane normal to rotor shaft axis, with axial width exceeding web root part thickness in (3.5÷5.0) times. 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 perpendicular to blade root radial axis makes, angle of α installation of the blade root defined in the range of values α=(18÷26)°. 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=(206.4÷296.8) [deg/m]. Besides, root inlet and outlet edges are made diverging to peripheral blade end with gradient G_{w. h.} of their connecting chord increase equal to G_w.h.=(6.9÷9.9)·10^-2 [m/m].

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

23 cl, 5 dwg