FIELD: aircraft engine engineering. SUBSTANCE: ring cooling profiled shield is mounted in the prechamber coaxially to a fairing positioned downstream of the turbine. The front part of the shield is positioned in a valve for hot gas upstream of maximum thickening of the fairing. The shield crosses a sector which is formed with two lines drawn from a point of nozzle generatrix at its minimum cross-section. The first line is tangential to the generatrix of the fairing at the its thickening. The second line crosses the generatrix of a contour separator at initial section of the fairing. EFFECT: improved design. 5 cl, 10 dwg
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