ROTOR SHAFT OF LOW PRESSURE COMPRESSOR OF TURBOJET ENGINE Russian patent published in 2015 - IPC F04D29/32 F01D5/06 

FIELD: engines and pumps.

SUBSTANCE: invention relates to aircraft engine building, namely to low pressure compressors of aircraft TJEs. The shaft of the low pressure compressor is implemented as the step drum and disk structure comprising no four disks maximum. Each disk comprises the rim passing into the annular blade strengthened by the massive hub fitted with the central hole which accrues step-by-step radially from the first to the fourth disk. 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 the groove of the first 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 α = (19÷25)°. Rims of the first three disks form with reference to the middle plane of the blade two asymmetrical shelves by which directly or through cylindrical spacers the disks are integrated into 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 conic circular elements in one piece integrated with the companion conic diaphragms of journals of the front and back supports. Generatrix of the conic element of the first stage disk is inclined to the shaft axis at the angle β.

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.

6 cl, 3 dwg