SEAL ASSEMBLY IN A TURBINE ENGINE (OPTIONS) Russian patent published in 2018 - IPC F01D11/04 F01D5/08 

FIELD: machine building.

SUBSTANCE: seal assembly between a hot gas path and a disk cavity in a turbine engine comprises a non-rotatable guide vane assembly, a rotatable blade assembly and an annular wing element. Non-rotatable guide vane assembly includes a series of guide vanes and an inner shroud, and the rotatable blade assembly adjacent to the guide vane assembly and includes a series of blades and a turbine disk that forms a part of a turbine rotor. Annular wing element is radially disposed between the hot gas path and the disk cavity, extends generally along the axis from the blade assembly to the guide vane assembly, and includes a plurality of circumferentially spaced apart flow channels. Flow channels extend through the annular wing element from its radially inner surface to its radially outer surface and pump a cooling fluid from the disk cavity toward the hot gas path during engine operation. On its way through the wing element, the flow channels are curved in the circumferential direction opposite to a direction of rotation of the turbine rotor to scoop the cooling fluid from the disk cavity into the flow channels. In another embodiment, the flow channels include inlet portions inclined opposite to the direction of rotation of the turbine rotor to scoop the cooling fluid from the disk cavity into the flow channels. Outlets of the flow channels are inclined in the direction of rotation of the turbine rotor, allowing the cooling fluid to be discharged from the flow channels in the direction of rotation of the turbine rotor.

EFFECT: group of inventions allows to reduce the absorption of hot gas into the cavity for the turbine disk.

16 cl, 6 dwg