TWISTED GAS TURBINE ENGINE AERODYNAMIC PROFILE HAVING TWISTED RIB Russian patent published in 2018 - IPC F01D5/14 F01D5/18 

FIELD: machine building.

SUBSTANCE: gas turbine engine blade comprises an aerodynamic profile having an outer and inner surface of the trough and back of the blade, and also the first and second ribs extending between the inner surface of the trough of the blade and the inner surface of the blade back. Aerodynamic profile is twisted from its lower to the upper end. First rib forms part of the tortuous cooling channel and is twisted from its lower end to the upper end. First rib is tapered between the inner surface of the trough of the blade and the inner surface of the blade back, taper provides an increase in the angle of intersection of the surface of the first rib with one of the inner surfaces of the trough of the pen and the back of the feather in the corner of the tortuous cooling channel formed by the first rib and one of the inner surfaces of the trough of the feather and back of the feather, as compared to the unbroken rib. Taper is symmetrical with respect to the first longitudinal axis of the rib. Outer surface of the trough of the blade, the outer surface of the back of the blade and the first rib are cast in one piece. Second rib is twisted from its lower to the upper end and tapered in a tapering manner along its full length between the inner surface of the trough of the blade and the inner surface of the blade back. Tapers of the first rib and the second rib are oppositely directed. In another embodiment of the blade, the first and second ribs define respectively the first and second longitudinal axes and comprise respectively the first and second front end sides and the first and second rear end sides. In the radial cross-section of the aerodynamic profile at the lower end of the first and second ribs, respectively, the first and second longitudinal axis respectively define the first and second support axis. First front end and the first back edge are tapered to each other along the entire length of the first rib between the inner surface of the trough of the blade and the inner surface of the blade back, the constriction being symmetrical with respect to the first longitudinal axis. In another radial cross-section of the aerodynamic profile, the respective first and second longitudinal axes are not parallel to the first and second reference axes, thereby forming an angle of intersection with the first and second support axes. In another embodiment, the first and second longitudinal axes are normal to both inner surfaces of the blade trough and back of the blade, and in at least one radial cross-section of the aerodynamic profile, the first longitudinal axis and the second longitudinal axis are not parallel.

EFFECT: invention makes it possible to simplify manufacturing and increase the strength of the gas turbine engine blade.

16 cl, 12 dwg