GAS TURBINE ENGINE BLADE MADE ACCORDING TO THE RULE OF DEFLECTION OF THE BLADE PROFILE WITH A LARGE FLUTTER MARGIN Russian patent published in 2023 - IPC F01D5/14 

FIELD: gas turbine engines.

SUBSTANCE: invention relates to a rotor blade of a gas turbine engine, containing a plurality of sections of the blade stacked on top of each other along the Z axis between the root part of the blade and the end part of the blade, defining between themselves the height of the blade, while each section of the blade contains a leading edge (21), a trailing edge ( 22), pressure side (19) and back side (18), a chord (25) determined by the length of the chord line, which is the section connecting the leading edge (1) and the trailing edge (2), and the maximum profile deflection (28), determined by the maximum the length of the section perpendicular to the chord line and connecting the point of the chord line and the point of the bend line formed by all points located at an equal distance from the back side (18) and the pressure side (19) in the section, while according to the invention, the ratio between the maximum deflection of the profile and the chord at half the height of the blade is from 25% to 40% of the ratio between the maximum deflection of the profile and the chord at the root of the blade, and the ratio between the maximum profile bend and chord at the end of the blade is from 25% to 40% of the ratio between the maximum deflection of the profile and the chord at the root of the blade.

EFFECT: invention is aimed at increasing the flutter margin without increasing the weight of the blade.

11 cl, 6 dwg