GAS TURBINE ENGINE COOLED TURBINE Russian patent published in 2014 - IPC F01D5/18 

FIELD: engines and pumps.

SUBSTANCE: cooled blade comprises outer case with shroud liner and nozzle diaphragm with peripheral holes communicated with cooling air feed system, rotor with working blades with cooling channels and ledge over perimeter of end face surface to make an exposed end chamber. Shroud liner and end face surface of every blade has bypass opening. valves have inner webs with inlet openings while blade end chamber is proved with separation rib. Said web is arranged with clearance relative to end face surface to make a summing chamber. Separation rib is arranged inside end chamber in the blade rotation plane at 0.3-0.7 of the blade axial profile size to make open front and rear cavities. Outlet holes in the blade end surface are made in rear cavity. Summing chamber communicates via inner web inlet holes with blade cooling channels and, via outlet holes in end surface with rear cavity and gas-cir circuit via holes in blade trailing edge. Outlet holes in shroud liner are made above front cavity. Total area of outlet holes of summing chamber makes 3-6 of total area of inlet holes in inner web.

EFFECT: longer life, decreased gas leaks via radial clearance, higher turbine efficiency.

3 cl, 7 dwg