PART AND ASSEMBLY UNIT OF HIGH-PRESSURE TURBINE NOZZLE ASSEMBLY Russian patent published in 2021 - IPC C23C28/00 C23C4/73 C23C4/11 

FIELD: machine building.

SUBSTANCE: invention relates to aircraft engine building, particularly, to design of parts and assembly units (PAU) of high-pressure turbine nozzle assembly (HPT NA) of high-pressure turbine engine, mainly for highly manoeuvrable airplanes. Detail of assembly unit of high-pressure turbine nozzle assembly is made of heat-resistant and heat-resistant nickel-based alloy with heat-protective coating, which contains metal sublayer, ceramic underlayer and upper ceramic layer, wherein metal sublayer with thickness from 35 to 130 mcm is made by plasma sputtering of nickel-based powder alloy containing 18–25 % of cobalt, 13–22 % of chromium, 10–15 % of aluminium and 0.1–0.9 of yttrium, besides, volume porosity and volume content of inclusions of oxides in layer in total amount to not more than 7 %, ceramic sublayer with thickness from 120 to 220 mcm is made by plasma spraying of powder material based on zirconium dioxide, containing 7.5–11.5 % dysprosium oxide, wherein porosity of layer is from 5 to 20 %, and upper ceramic layer with thickness of 30 to 130 mcm is made by plasma spraying of powder material based on zirconium dioxide containing 45–65 % of gadolinium oxide, wherein porosity of layer is from 5 to 20 %.

EFFECT: technical result of the invention is increase of service life of gas-turbine engine PAU of HPT NA till 2000 hours due to reduction of temperature on the surface of PAU by application of multilayer heat-protective coating with upper ceramic layer having low heat conductivity on the surface that is most in contact with gas flow.

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