HIGH-TEMPERATURE GAS TURBINE Russian patent published in 2009 - IPC F01D1/00 

FIELD: engines and pumps.

SUBSTANCE: high-temperature gas turbine has its nozzle vane upper flange rear end face, if seen streamwise, furnished with a slot facing the turbine stage split ring and formed by arcs. The said slot outlet communicates with the slit-like circular air space arranged between the upper flange and split ring. The said split ring accommodates a perforated tape intended for blowing over the split ring front part. The said ring rear part features the holes inclined streamwise to feed cooling air to the turbine blading section. The nozzle vane upper flange rear end is locked axially by L-section lock ring.

EFFECT: higher reliability of high-temperature gas turbine.

1 cl, 4 dwg