FIELD: aviation; engine building.
SUBSTANCE: invention relates to aircraft engine building, in particular, to bench tests of a gas generator of an aircraft engine or a full-size aircraft engine, is intended for measurement of parameters of a working medium behind a combustion chamber (at the inlet of a high-pressure turbine). Cooled nozzle blade of a high-pressure turbine of a turbojet engine, comprising a hollow perforated feather with possibility of installing deflectors, and perforated outer and inner flanges. Hollow re-formed feather is made with front, middle and rear cavities with individual cooling systems, in addition, in the front cavity of the feather there are at least five channels for outputting the conductors for connecting the sensors, made integral with the deflector and the hollow perforated feather of the nozzle blade, at least five diffusers made in the form of cylindrical screens with the possibility of installation of sensors in them are located on the input edge of the feather.
EFFECT: invention provides higher reliability and manufacturability when preparing a nozzle blade with sensors for measuring parameters.
1 cl, 3 dwg
