GAS TURBINE ENGINE Russian patent published in 2014 - IPC F01D9/04 

FIELD: engines and pumps.

SUBSTANCE: gas turbine comprises stator blade to direct hot combustion gases to rotor blades. Stator blade comprises shroud arranged at the blade radially inner side relative to engine rotational axis. Said shroud has the part of trailing edge downstream of hot gas flow behind the stator blade. Besides, gas turbine incorporates structural and cooling system to direct coolant to top upstream end of the shroud trailing edge. Said edge is turned radially inward relative to turbine rotational axis. Structural and cooling system also directs said coolant axially towards the edge bottom downstream end. Said coolant cools training edge part at flowing over said edge. Said edge includes turbulence promoters to up the heat transfer from the part of trailing edge at coolant flowing over said edge. Said turbulence promoters extend axially across the turbine rotational axis. The edge turned radially inward comprises several wall webs extending axially to separate said edge to several separate cooling channels extending axially. Turbulence promoters of said edge are arranged in cooling channels.

EFFECT: higher efficiency of cooling.

11 cl, 6 dwg