FIELD: machine building.
SUBSTANCE: invention relates to aircraft engine building, particularly, to double-flow turbojet engines nozzles. System of nozzles for working gases of double-flow turbojet engine without mixing of circuits flows comprises two cold channels changing their cross-section from semi-ring behind engine fan to rectangle at outlet and one hot channel of round cross section located between cold channels. Channels terminate by nozzles, which are devices for control of value and direction of working gas jet. Invention makes it possible to fit nozzle into tail part of aircraft plane by flying wing or tailless and control thrust vector in cold channel, leaving hot channel in form of extension pipe of minimum weight. System of nozzles for working gases produced by gas generator plant of double-flow turbojet engine in aircraft includes channels and nozzles. Channels of cold circuit discharge air flow from engine fan and are formed by cross-sections having shape of semi-ring at output from cold external circuit of engine, with smooth transition of section shape to rectangle located by wide side along rear edge of aircraft wing. Upper and lower edges of such rectangle contain flaps varying the cross-section area on the nozzle edge and/or the direction of air outlet from it. Channel of hot inner circuit removes hot gases from engine gas generator and is formed in cross sections by circles. Longitudinal axis of channel of hot circuit is made in the form of smooth transition from axis of engine to axis parallel to plane of symmetry of aircraft or forming with such axis small angle to the outside in order to reduce turning moment at failure of engine.
EFFECT: invention allows reducing aerodynamic resistance and weight of aircraft.
6 cl, 16 dwg
