REVERSE TURBINE NOZZLE RING Russian patent published in 2018 - IPC F01D1/30 F01D25/24 F01D9/02 

FIELD: machine building.

SUBSTANCE: nozzle apparatus of reversible turbine includes forward nozzle device located on lower tier of turbine, reverse nozzle device located in upper tier of turbine, and intermediate casing. On outer side of intermediate body sectors of nozzle reversing device are fixed with the help of lower platforms, and on inner side of intermediate body sectors of nozzle device of direct travel are fixed with the help of upper platforms. Lower platform of each sector of nozzle reversing device is equipped with front hitch that enters annular groove of intermediate housing, which has supporting cylindrical surfaces, is provided with rear cylindrical bearing surface supported on surface of intermediate body and is provided with radial protrusion. Radial protrusion is made on rear of lower platform from side facing motor axis, and enters longitudinal groove of intermediate body and simultaneously engages with radial projection of sector of nozzle device of forward stroke opposite. Each sector of nozzle reversing device is provided with through holes, passing through pen profiles of one of sector blades, with pins installed in them, ends of which enter blind holes of intermediate housing. On the side of upper platform of sector of nozzle reversing device, pins are fixed with the help of holding plates. Upper platform of each sector of nozzle direct-motion device comprises front hitch supported by cylindrical surface on inner annular rib of intermediate body, end ring groove under front hitch, mating with previous stage of direct-drive turbine, rear edge and radial protrusion. Rear fin rests on supporting surfaces of intermediate body: end face of its rear inner shoulder and cylindrical surface. Radial protrusion enters notch on rear end of intermediate housing and simultaneously engages with radial projection of sector of nozzle return device.

EFFECT: invention makes it possible to increase reliability of reversible turbine by reducing stresses on elements of nozzle apparatus.

1 cl, 6 dwg