METHOD FOR 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: gas turbine engine low-pressure compressor rotor shaft represents a drum-disc design composed of a four-stage, hence, four-disc structure. 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. At the second stage, mentioned unit is assembled 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 section 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. The exterior surface of the rim discs operate at an angle relative to the generator rotor shaft axis coinciding with the angle 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 of the third.

EFFECT: perfected manufacture parameters, higher efficiency and gas dynamic stability, doubled rotor shaft life without increase in the input of material.

20 cl, 2 dwg