NOZZLE SET FOR TURBINE OF GAS-TURBINE ENGINE Russian patent published in 1995 - IPC

FIELD: gas-turbine engineering. SUBSTANCE: in operation, the secondary air of the combustion chamber enters ring space 11 from space 13 through opening 14 and then flows to front space 12 of force blade 1 and pressurizes it. Simultaneously, the secondary air of the combustion chamber enters front space 12 of force blade 1 from space 15 from the side of the top shelf. A portion of air, which is fed from the side of the bottom shelf from space 11 through ring gaps, pressurizes the space defined by a shell and support 4 of the nozzle set. Pressure inside the space is lower than in space 11 as air is throttled at the inlet by the ring gaps. Air, which is fed from the space defined by the shell and support 4 through a group of perforation holes made in the shell, flows around the inner side of the bottom shelf and thus cools it. Next, air flows to the flowing part of the turbine through the perforation holes made in the bottom shelf of nozzle blade 1 and affords additional film cooling. EFFECT: improved design. 4 dwg