CHEVRON NOZZLE OF GAS TURBINE ENGINE Russian patent published in 2017 - IPC F02K1/46 F02K1/48 

FIELD: engines and pumps.

SUBSTANCE: chevron nozzle of a gas turbine engine includes the exhaust pipe and the nozzles of the outer and inner contours, which have chevrons of the triangular shape with profiled edges at the output. The chevrons of the outer contour nozzle are inclined at an angle 6-8° to the current line at the outer contour nozzle outlet, which is the middle line between the tangent to the inner contours of the outer contour nozzle and the tangent to the outer contours of the inner contour nozzle. The chevrons of the inner contour nozzle are inclined at an angle 4-6° to the current line at the inner contour nozzle outlet, which is the middle line between the tangent to the inner contours of the inner contour nozzle and the tangent to the outer contours of the central body.

EFFECT: invention allows to lower noise and to reduce aerodynamic losses during the operation of a gas turbine engine.

4 cl, 6 dwg