COMPRESSOR BLADE Russian patent published in 2020 - IPC F01D5/20 F01D11/08 

FIELD: engine building.

SUBSTANCE: compressor blade (70) for turbine engine. Compressor blade (70) comprises root fragment (72) located at a distance from fragment (100) of the end part of the blade by means of fragment (102) of the main part. Fragment (102) of main part is determined by: wall (88) of surface of back of blade, having surface (89) of back of blade, and wall (90) of surface of pressure side of blade, having surface (91) of pressure side of blade. Wall (88) of the back surface of the blade and wall (90) of the surface of the pressure side of the blade are found on inlet edge (76) and outlet edge (78). Fragment (100) of the end part of the blade comprises wall (106) of the end part of the blade, which stretches from inlet edge (76) of the blade to output edge (78) of the blade. Wall (106) of the end part of the blade defines signal ledge (110), comprising: first area (112) of the wall of the end portion of the blade, which extends from inlet edge (76); second region (114) of the wall of the end portion of the blade, which extends from output edge (78); and third area (116) of wall of end part of blade, which is drawn between first area (112) of wall of end part of blade and second area (114) of wall of end part of blade.

EFFECT: reduces overall loss in efficiency.

14 cl, 9 dwg