TRANSITION CHANNEL BETWEEN TWO STAGES OF TURBINE AND GAS-TURBINE ENGINE Russian patent published in 2012 - IPC F01D25/24 F01D9/06 

FIELD: engines and pumps.

SUBSTANCE: transition channel between the first stage of turbine and the second stage of turbine of gas-turbine engine contains the first inner and the second outer annular walls, at that the first wall contains inlet holes for gas injection inside channel for makeup of boundary layer. The first wall contains elements in the shape of annular sectors arranged within annular link forming annular space of gas distribution together with turbine crankcase element being external in relation to the link mentioned. Between space external to annular link and inlet holes there are installed means for leakproof gas supply including holes made in annular link and cavities provided in annular sectors, forming the first wall, and connected to inlet holes. Another invention of the group refers to gas-turbine engine containing above mentioned transition channel in which gas is removed from zone located at level of compressor upstream of transition channel, at that removed air forms a cold layer protecting the first wall.

EFFECT: improving efficiency of low pressure turbine and reducing leak of gas fluid medium supplied to inlet holes.

13 cl, 3 dwg