SHOCK ABSORBER FOR BLADES OF GAS-TURBINE ENGINE, ROTOR OF GAS-TURBINE ENGINE (VERSIONS), COMPRESSOR OF GAS-TURBINE ENGINE (VERSIONS), AND GAS-TURBINE ENGINE (VERSIONS) Russian patent published in 2013 - IPC F01D5/26 F01D25/06 

FIELD: machine building.

SUBSTANCE: shock absorber for gas-turbine engine compressor rotor blades. Shock absorber structure is adapted for arrangement between lower edge of platforms of two adjacent blades of gas-turbine engine and rotor disc rim, on which blades are installed. Shock absorber includes inertia load (11), base (13), the structure of which provides the possibility of its being supported on the above rim, and spring (12). Spring connects inertia load to base. At least inertia load (11) is made from composite material. Shock absorber is provided at least on one free end of the base or the inertia load with a piece of spongy plate (14, 15), which forms a limit stop or a fixing hook that turns out to be pressed either (14) to radial stiffener of the blade, or (15) to rear edge of the disc rim.

EFFECT: possible installation of a shock absorber into hard-to-reach places and performance of maintenance in situ at simultaneous restriction of friction of contact parts, which allows in its turn reducing wear rate of the latter.

14 cl, 11 dwg