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

FIELD: engines and pumps.

SUBSTANCE: invention relates to engine building. GTE low-pressure compressor rotor third stage disc is made in form of single component, including rim changing into circular web, reinforced by hub, having central opening. Disc radius R_d from axis to rim outer surface in web middle plane is (0.59÷0.84) of flow part peripheral contour in said plane radius R_r.p. Rim is asymmetrically connected with disc web with formation of different-arm circular flanges. Rear flange is made with possibility of permanent connection with next stage disc via spacer. For permanent joint with the disc of the next stage bores for fasteners are made via said spacer in disc web. Disc ring is provided with the system of grooves for securing of blades. 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)°. Slots are uniformly spaced apart along disc perimeter and made with side faces in cross section, forming element of lock joint with blade root. Web is provided with conical circular element, made with generatrix inclination angle to disc geometrical axis of not less than 48°. Enabling higher efficiency and expanded range of compressor gas-dynamic stability modes for 2.1 % while increasing disc service life in 2 times.

EFFECT: enabling higher efficiency.

6 cl, 4 dwg