FIELD: aeronautical engineering. SUBSTANCE: bladeless nozzle set for aircraft gas-turbine engine at axial delivery of working medium from combustion chamber includes circular housing which is provided with curvilinear passages for supply of working medium to turbine blades; sections of these passages are oriented in radial direction. Each passage has radially oriented section and center line running in plane perpendicular to plane of rotation of turbine wheel which is located at angle of 40 to 60 deg. Relative to meridian plane passing through center of passage inlet section. Area of inlet section exceeds area of outlet section by at least three times. EFFECT: reduced losses of average mass velocity. 5 dwg
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