GAS TURBINE BLADE Russian patent published in 2020 - IPC F01D5/14 F01D9/02 F04D29/38 

FIELD: turbines or turbomachines.

SUBSTANCE: invention relates to a gas turbine plant blade comprising a feather extending radially from the blade root to the blade rim, determining the swing, equal to 0 % for blade root and 100 % for blade rim, and continuing in radial direction from inlet edge to outlet edge, which limits the chord with the axial length of the chord defined by the axial length of the straight line connecting the leading edge and the output edge of the blade depending on the span. Invention is characterized in that axial length of chord increases from 80 % of span to 100 % of span. Bending of input (9) and output (10) edges is defined by curvature of folding line (12), which is a line on trough (11) of feather (1) extending from 0 % span to 100 % of span in axial position of 50 %±5 % of axial length (6) of chord, wherein folding line (12) is bent in area between 50 % and ±10 % of span and 100 % of span so that fold line (12) by 100 % span makes an angle α with virtual plane (13), oriented orthogonal to radial direction, wherein α angle is located in plane defined by folding line and radial direction, and angle has the α following expression: (12.5°±2.5°)≤α≤(25°±5°).

EFFECT: improved blade has substantially better vibration state and is obviously resistant to vibration excitation; this leads to effective improvement of aerodynamic state and obviously increases service life.

10 cl, 4 dwg