HIGH-TEMPERATURE MULTI-STAGE GAS TURBINE Russian patent published in 2009 - IPC F01D5/08 F01D5/18 

FIELD: engineering industry.

SUBSTANCE: high-temperature multi-stage gas turbine includes cooled rotor blade and rotor blade with an uncooled wing, which is located downstream the cooled rotor blade. Rotor blade with an uncooled wing is provided with a prolonged root as well as with front and rear sealing ribs and a lock. On lateral surfaces of the root of rotor blade with uncooled wing there made are elements intensifying cooling, for example pins. From the leading edge of blade with uncooled wing there located are sealing plates provided with cooling air supply channels connected to rotor air pocket at the inlet, and at the outlet - through the channels made in front streamwise sealing ribs of the root to air pocket formed by roots of neighbouring blades. Air pocket is connected through channels made in rear streamwise sealing ribs to turbine gas pocket. Channels made in front and rear ribs are made tangential to lateral surface of the root.

EFFECT: improving reliability of high-temperature gas turbine owing to reducing temperature of the root and root sections of wing of rotor blades.

3 dwg