GAS-TURBINE BLADE PROVIDED WITH COOLING CIRCUITS Russian patent published in 2007 - IPC F01D5/18 

FIELD: aircraft engines.

SUBSTANCE: proposed blade has at least one central cooling circuit in central part of feather incorporating at least first and second cavities stretched in radial direction along concave surface of blade feather and at least one cavity stretched along convex surface 1b of blade feather. Inlet hole is disposed at radial end of first cavity 2 on concave end of feather to admit cooling air to first cooling circuit. First duct provides communication between other radial end of first cavity and adjacent radial end of cavity on convex end of feather. Second duct provides communication between other radial end of cavity on convex end of feather and adjacent radial end of second cavity on concave end of feather. Outlet holes communicate with mentioned second cavity and with concave surface of feather.

EFFECT: ability of maintaining constant temperature field in blade cooling areas in case air fails to escape through convex surface of feather.

11 cl, 4 dwg