HIGH-TEMPERATURE TURBINE OF GAS TURBINE ENGINE Russian patent published in 2012 - IPC F01D25/24 

FIELD: engines and pumps.

SUBSTANCE: high-temperature turbine of gas turbine engine includes nozzle blades and rotating blades located downstream of gas flow. Sectors of the main split ring and external housing of turbine with radial reinforcing rib are installed on outer side from rotating blades. Nozzle blades are fixed in axial direction with a retaining ring with a radial rib, which contacts the outlet edge of upper flanges of nozzle blades. Intermediate split ring that has N-shape in cross section and that is fixed on inner side from radial reinforcing rib is located between sectors of the main split ring and external housing. Sectors of the main split ring are provided with three-chamber cooling system separated from inner air cavity of intermediate N-shaped ring with a belt with air supply channels. Channels of each cooling chamber are displaced forwards in gas flow direction relative to inlet of cooling hole of the sector, and ratio of the number of sectors of the main split ring to the number of sectors of intermediate split ring is equal to 2.

EFFECT: invention allows improving reliability of gas turbine engine.

3 dwg