FAN BLADE OF GAS TURBINE ENGINE Russian patent published in 2018 - IPC F01D5/14 F04D29/38 

FIELD: motors and pumps.

SUBSTANCE: fan blade of gas turbine engine consists of base, metallic covering forming pressure side, back edge and entering edge, and core strength member installed in the cavity inside the metallic covering and damping material in form of panels with comb cells. It contains end plug, intermediate flute partitions are installed between the base and the end plug. Tube can be made elliptical in cross section. Comb cells can be filled with aluminosilicate hollow microspheres. Near the entrance edge in the cavity of blade can be installed a metal tube, divided by partitions into sections, which are filled with aluminosilicate hollow microspheres. Tube can be made elliptical in cross section. In the intermediate partitions, holes can be made for the passage of metal tube into which dampers are installed.

EFFECT: simplification of design, increase in the impact and vibration strength.

5 cl, 13 dwg