GAS TURBINE ENGINE HIGH-TEMPERATURE TURBINE Russian patent published in 2014 - IPC F02C7/06 F02C7/12 

FIELD: engines and pumps.

SUBSTANCE: high-temperature turbine outer housing accommodates nozzle blade, split sector ring arranged downstream of gas flow, working blade and sealing tongues on upper platform. The latter makes the labyrinth seal with split ring inner surface. Band is fitted between turbine housing and nozzle blade lock ring to make circular closed chambers between said band and housing. Split ring has conical ring directed to nozzle blade to make the circular air chamber. Said chamber inlet is communicated with nozzle blade air cooling chamber while its outlet is communicated with the turbine flow section via slotted circular chamber. Circular chamber is composed of nozzle blade top platform and conical rib. Slotted chamber is located on inner side from working blade top platform. Ratio of the pitch of circular micro ledges on split ring inner surface to radial clearance between front tongue at working blade top platform and split ring makes 1…2. Ratio of the height of circular micro tongues to radial clearance makes 0.8…1.8 Ratio of the length of circular micro tongue end surface to radial clearance makes 0.3…0.8. Ratio of radial clearance between rear tongue on working blade top platform and split ring to radial clearance between front tongue on working blade top platform and split ring makes 1.5…2.5.

EFFECT: higher reliability.

2 dwg