GAS TURBINE ENGINE LOW PRESSURE COMPRESSOR 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. Gas turbine engine low-pressure compressor (GTE LPC) rotor shaft first stage impeller includes disk, 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. Disk rim is connected with web to make different-arm circular conical inclined flanges. Rim outer surface is made with inclination relative to rotor shaft axis, which radius is monotonously varies towards working fluid flow with radial expansion gradient of G_on=(0.32÷0.46) [m/m]. Disk rim is equipped with set of blades fixation grooves uniformly distributed along disk 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 blade root installation defined in range of values α=(16.8÷24.1)°. 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 gradient G_u.p=(144.9÷208.3) [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 decreases on height of feather to peripheral end with gradient G_u.t.=(1.0÷1.44)·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.

19 cl, 6 dwg