The rotor shaft low-pressure compressor of the turbojet engine, NODE CONNECTIONS ROTOR DRIVE SHAFT low-pressure compressor of the turbojet engine, spacer CONNECTION UNIT DRIVE SHAFT ROTOR low-pressure compressor of the turbojet

摘要

The invention relates to the field of aircraft engine, namely, a low pressure compressor turbojet aircraft. Val low-pressure compressor drum-formed stepped disk structure comprising no more than four discs. Each disk includes a rim, the annular web rolling, reinforced massive hub with a central opening. blade disc thickness not less than three times less than the axial width of the hub. Simply supported on the rim web is provided with a tilt relative to the shaft axis slots for mounting shanks of rotor blades. The slots are evenly spaced around the perimeter of the disc. The longitudinal axis of each slot forms a disc of the fourth stage with the rotor shaft axis in projection on an axial notional plane normal to the radial axis of the pen, the angle α of the shank of the blade. The rim of the fourth stage disc forms two equal-shelf, the total axial width of which is commensurate with the width taken of the projection of the blade. The disc of the fourth stage is detachably connected with web through spacer disk shelf preceding stage to form a cantilevered circumferential shell connecting the drive to the power core hardness drum-disk design of the rotor shaft. The shaft is made up of one-piece assembly sections. The web drive the first stage from the front side and the third stage disk web from the rear side are provided with conical ring elements integrally connected with the mating conical diaphragms pivots front and back support. The inventive node wheels connected via an annular spacer. The spacer is provided with L-shaped in a cantilever limb, forming an annular flange with bores for the passage of system elements detachably connected to the disk radially spaced apart flange perimeter. The technical result consists in improving the geometrical configuration and spatial rigidity node elements compound discs and power parameters of a drum design of disk-rotor shaft turbojet CPV while increasing overall compactness, adaptability, maintainability and reduction in material consumption and labor intensity of assembly of the rotor shaft. 3 bp f-ly, 10 ZP f ly-3-yl.