ROTOR OF COMPRESSOR OF GAS TURBINE ENGINE Russian patent published in 2019 - IPC F01D5/06

Abstract RU 2696173 C1

FIELD: machine building.

SUBSTANCE: invention relates to machine building, particularly, to rotor of compressor of aircraft gas turbine engine. Gas turbine engine compressor rotor includes disks, front and rear disc ends, intermediate rings with fixation pins. At least on one of discs on rear end of its rim there is a recess with length in circumferential direction L1 making 4.0…4.7 of fixing pin diameter D, dimension L2 from recess to rounding with radius R1 in groove base in disc for tail of dovetail blade is 0.3…0.5 diameter D fixation pin, depth of depression DD is equal to 1.3…1.7 of the fixing pin diameter D, and the recess height H is 1.1…1.3 times the diameter D of the fixation pin.

EFFECT: disclosed invention allows to unload the critical zone of the disc, increase its cyclic durability, and therefore improve the reliability of the compressor rotor in the gas turbine engine.

1 cl, 3 dwg

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RU 2 696 173 C1

Authors

Burtseva Irina Valerevna

Bugreeva Svetlana Ilinichna

Gabova Tamara Aleksandrovna

Dates

2019-07-31—Published

2018-07-31—Filed