CONTINUOUS TRANSIENT CHANNEL BETWEEN HIGH-PRESSURE TURBINE AND LOW-PRESSURE TURBINE OF DOUBLE-FLOW AIRCRAFT ENGINE Russian patent published in 2013 - IPC F01D25/30 

FIELD: engines and pumps.

SUBSTANCE: continuous annular transient channel between a high-pressure turbine and a low- pressure turbine with expansion degree of more than 1.6 and an equivalent opening angle of a flat diffuser of more than 12° includes external and internal perforated walls. Flow swirl after the high-pressure turbine runner is transformed in the direction of its amplification at walls and attenuation in the centre. The swirl is transformed due to shaping of a stage of the high-pressure turbine and due to a swirling device located after the runner of the high-pressure turbine with the height of 10% of the channel height to 5% of the height on internal and external walls of the channel, or due to a twisting-untwisting device of total height.

EFFECT: invention allows reducing losses in a transient channel between high-pressure and low-pressure turbines.

3 cl, 6 dwg