FIELD: engine devices and pumps.
SUBSTANCE: convergent-divergent nozzle of the turbomachine comprises an annular central structural element and an annular housing coaxially arranged around central structural element so as to limit an annular channel of the engine gas flow there with it. Between critical section of the nozzle and nozzle outlet section, an outer profile of central structural element and an inner profile of the housing are formed in longitudinal section, by means of curves of lines, whose radii of curvature have value of second order derivative of function y (X) determining the shape of said curves of lines relative to axial position along the corresponding curve of the line. The corresponding radii of curvature of curves of the lines are identical in absolute value. Other inventions of the group refer to the bypass turbojet engine and the turboprop comprising said nozzle.
EFFECT: increased aerodynamic properties of the nozzle.
5 cl, 3 dwg
