NOZZLE BLADE OF A TURBINE OF A GAS TURBINE ENGINE Russian patent published in 2022 - IPC F01D5/14 F01D5/28 

FIELD: aircraft engine building.

SUBSTANCE: invention relates to the field of aircraft engine building, and in particular to the design of the nozzle blades of the turbine of a gas turbine engine (GTE). The GTE turbine nozzle blade contains an outer aerodynamic profile made of ceramic material, a hollow metal deflector and an intermediate deflector installed between them, provided with protrusions on the outer and inner surfaces, forming channels for cooling air with opposite surfaces. The intermediate deflector is made of ceramic or composite material. The inner cavity of the metal deflector is in communication with the cavity for supplying cooling air to the turbine rotor.

EFFECT: reduction of air consumption for cooling the turbine nozzle blade, reduction of gas-dynamic and heat losses in the turbine nozzle apparatus of the gas turbine engine, as well as the possibility of increasing the gas temperature in front of the turbine to stoichiometric values, which leads to an increase in the parameters of the gas turbine engine cycle and an increase in the efficiency of the turbine and gas turbine unit as a thermal machines in general.

2 cl, 2 dwg