COOLED NOZZLE BLADE OF HIGH-PRESSURE TURBINE OF TURBOJET ENGINE WITH REPLACEABLE NOSE FOR BENCH TESTS Russian patent published in 2022 - IPC F01D25/12 

FIELD: aircraft engine construction.

SUBSTANCE: invention relates to the field of aircraft engine construction, in particular to bench tests of a gas generator of an aircraft engine or a full-size aircraft engine; it is designed to measure parameters of working fluid behind a combustion chamber (at an inlet to a high-pressure turbine). In a cooled nozzle blade, a hollow perforated pen is made prefabricated, containing a blade and a replaceable insert, wherein the blade is made with two cavities with individual cooling systems, and the replaceable insert acts as an inlet edge of the blade with a ledge relatively to a blade profile, while it is made with an internal cavity and a built-in deflector with an individual cooling system, and a bracket is installed on the outer part of the replaceable insert. In addition, a rectangular groove is additionally made on the outer shelf of the blade with the possibility of installing the outer part of the replaceable insert into it, repeating its shape, and a blind centering hole is made on the inner shelf of the blade with the possibility of fixing a cylindrical protruding element located on the bottom of the replaceable insert in it. Additionally, the inlet edge of the replaceable insert contains at least five diffusers with the possibility of installing sensors in them and at least five outlet channels of sensor connection conductors.

EFFECT: invention provides an increase in the reliability and manufacturability of a cooled nozzle blade of a high-pressure turbine of a turbojet engine with a replaceable nose for bench tests, used in the preparation.

1 cl, 3 dwg