METHOD OF PRODUCING A ROTOR SHAFT OF LOW-PRESSURE GAS TURBINE ENGINE COMPRESSOR AND ROTOR SHAFT OF LOW-PRESSURE COMPRESSOR, MADE ACCORDING TO THIS METHOD (VARIANTS) Russian patent published in 2017 - IPC F04D29/32 F01D5/06 

FIELD: engines and pumps.

SUBSTANCE: rotor axis KND GTD ("КНД ГТД") is perform as reel-disc, while assembling four-stage (by number of discs) construction. The shaft is made in three steps. At the first stage, the assembly units, i.e. the shaft front and rear bearing journals, discs and spacers are produced. At the second stage, mentioned units are gathered to three mounting sections to be coupled to compose the rotor shaft. Every section is a nonseparable structure. The front bearing journal, first and second stage discs and spacer are fitted in the first section. The second section includes the third stage disc, rear trunnion bearings and spacer. The third section - the fourth stage disc. In the third step, the sections are sequentially connected via spacers and complete the installation by attaching the drive of the fourth stage. Discs at all levels include the rim, rolling in the ring blade to the hub. Radius R_d2 of the first stage disc of the rotor shaft to the outer surface of the rim, in the middle plane of blade (0.54÷0.77) of radius R_f.p. of peripheral circuit of flow part. The exterior surface of the rim discs operate at an angle relative to the generator of rotor shaft axis coinciding with the angle of forming the internal flow path part. The number and frequency of placement slots for rotor blades of increase in the direction of the working fluid flow from the first drive to the third.

EFFECT: improvement of technological parameters for manufacturing a low-pressure compressor necessary to increase the efficiency, and expanding the gas-dynamic stability margin in the full range of compressor operation modes with a 2-fold increase in the rotor shaft resource without increasing the material consumption of the compressor.

19 cl, 2 dwg