ROTOR SHAFT OF LOW PRESSURE COMPRESSOR OF TURBOJET ENGINE, CONNECTION ASSEMBLY OF ROTOR SHAFT DISKS OF LOW PRESSURE COMPRESSOR OF TURBOJET ENGINE, SPACER OF CONNECTION ASSEMBLY OF ROTOR SHAFT DISKS OF LOW PRESSURE COMPRESSOR OF TURBOJET ENGINE

摘要

FIELD: engines and pumps.SUBSTANCE: invention relates to air-engine building. The shaft of the low pressure compressor is implemented as the stage drum and disk structure comprising no four disks maximum. Each disk comprises the rim passing into the circular blade strengthened by a massive hub. Disk blade thickness is minimum three times less than axial width of the hub. Supported by the blade the rim is fitted with the system of grooves inclined with reference to the shaft axis for installation of shafts of working vanes. Grooves are evenly spaced along the disk perimeter. The longitudinal axis of each groove of the fourth stage disk forms with the rotor shaft axis in a projection to the conditional axial plane, normal to a wing axis, the angle ? of installation of the vane shaft. The rim of the fourth stage disk forms two equal-arm shelves the total axial width of which is accepted to be comparable with the vane wing projection width. The disk of the fourth stage is split connected by the blade through the spacer to the disk shelf of the previous stage with formation of the console circular shell connecting the disk with the load bearing frame of rigidity of the drum and disk structure of the rotor shaft. The shaft is assembled from one-piece assembly sections. The blade of the first stage disk from the frontal side and the blade of the third stage disk from the back are fitted with the circular elements in one piece integrated with the companion diaphragms of journals of the front and back supports. In the offered assembly the disks are connected through the circular spacer. The spacer is fitted with L-shaped (in the cross-section) console bend forming a circular flange with the system of holes for passing of the elements of demountable connection with the disk which are radially spaced along the flange perimeter.EFFECT: increase of efficiency and increase of gyroscope position pickoff reserve in all operating modes of the compressor at increase of a resource of the low pressure compressor rotor shaft without increase of material capacity.9 cl, 3 dwg