TURBINE BLADE WITH PIN SEAL SLOT Russian patent published in 2018 - IPC F01D5/14 F01D11/00 

FIELD: engines and pumps.

SUBSTANCE: turbine blade of a gas turbine engine having a turbine disk with an axis includes an airfoil having a leading edge and trailing edge and a pressure side and suction side, a blade shank and a flange between the airfoil and the shank. Flange includes a pressure side flange and a suction side flange. Pressure side flange, which includes a pressure side inclined surface and a pressure side seal slot, which extends into the pressure side flange from the pressure side inclined surface and is located at an angle of three to ten degrees radially relative to the axis of the turbine disk. Pressure side seal slot includes a pressure side flat seal surface that extends along the pressure side inclined surface and inclines radially relative to the axis of the turbine disk. Suction side flange extends in the direction opposite from the pressure side flange and includes a suction side inclined surface and a suction side seal slot, extending into the suction side flange from the suction side inclined surface and located at an angle of three to ten degrees radially relative to the axis of the turbine disk. Suction side seal slot includes a suction side flat seal surface that extends along the suction side inclined surface and inclines radially relative to the axis of the turbine disk. Other inventions of the group relate to turbine disk assemblies and a gas turbine engine including said turbine blade.

EFFECT: group of inventions reduces the concentration of stresses on the turbine blade due to the possibility of using a longer rod seal.

10 cl, 7 dwg