GAS TURBINE ENGINE LOW-PRESSURE COMPRESSOR ROTOR SECOND 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 second stage disc is made in form of single component, including rim changing into circular web, reinforced by hub, having central opening. Said ring is asymmetrically connected with disc web to make different-arm circular conical inclined flanges. Disc rim is made with radius increasing towards working fluid flow in LPC axial section and rim outer surface generatrix angle relative to rotor shaft axis, identical to axial angle relative to same flow section inner circuit generatrix axis. Disc radius R_d from axis to rim outer surface in web middle plane is (0.54÷0.77) from radius R_p.p. of flow part peripheral contour in said plane. 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=(19÷27)°. Slots are uniformly spaced apart along disc perimeter with angular frequency of Y_u=(6.0÷8.2) [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.

17 cl, 4 dwg