GAS TURBINE ENGINE LOW-PRESSURE COMPRESSOR ROTOR LAST STAGE DISC 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 last stage disc is made in form of single component, including rim changing into circular web, reinforced by hub, equipped with central opening. Rim is symmetrically connected with disc web with formation of equal-arm circular flanges. Disc web can be articulated via spacer with the disc flange of the previous stage. Disc rim is made with radius increasing towards working fluid flow in LPC axial section and with rim outer surface generatrix angle φ=(1.8÷3.4)° relative to rotor shaft axis. 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, perpendicular to blade foil lengthwise axis, blade root installation angle of α, defined in range of values (20.1÷29.2)°. Slots are uniformly spaced apart along disc perimeter with angular frequency of Y_u=(5.8÷7.9) [unit/rad] and are made with side faces in cross section, forming element of lock joint with blade root. 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.

3 cl, 4 dwg