GAS TURBINE ENGINE ROTOR BLADE Russian patent published in 2019 - IPC F04D29/32 F01D5/14 

FIELD: physics.

SUBSTANCE: rotor blade of gas turbine engine, comprising aerodynamic profile defined by flat sections of aerodynamic profile laid in radial direction, wherein each section of aerofoil is located radially at height H, where the height H is expressed as a percentage of the total height of the aerofoil section and is identified by its angle λ sweep and its inclination angle in tangential direction ν, where angle λ sweep varies depending on height H so that angle λ sweep reaches maximum value at height HλM, wherein the value HλM lies in range of 5–40 %, and angle λ sweep increased from 0 % to HλM, and where inclination angle of blade in tangential direction ν varies depending on H such that said angle ν is a decreasing function of the height H for the heights H lying in range from 0 % to the value Hν1, wherein value Hν1 lies in range of 10–40%.

EFFECT: higher efficiency and reduced dynamic stresses.

8 cl, 7 dwg