REPAIR ELEMENT FOR GAS TURBINE BLADE ASSEMBLY AND REPAIR METHOD OF DAMAGED BLADE OF GAS TURBINE BLADE ASSEMBLY Russian patent published in 2020 - IPC F01D5/00 

FIELD: turbines or turbomachines.

SUBSTANCE: repair element (200) comprises an inner platform portion (201) configured to replace a portion of the inner platform of the damaged blade, an outer platform portion (202), made with possibility of replacement of damaged platform outer platform, and aerodynamic part (204), connecting sections (201, 202) of internal platform and external platform and made with possibility of replacement of front edge part or rear edge part of damaged blade. Inner platform (201) section is made so that it extends to edge of first ring or blade unit ring of damaged blade ring sector, and external platform section (202) is made so that it passes to the edge of the second blade or sector of the blade unit ring of the damaged blade. Inner platform section (201), outer platform section (202) and aerodynamic part (204) are made with provision of repair element (200) insertion into blade unit (100) by purely translational movement, performed along the direction of introduction and having a component parallel to axes (153) of first and second rings or sectors of rings (150, 160).

EFFECT: disclosed is a repair element for a gas turbine blade assembly and a method of repairing a damaged blade of a gas turbine blade assembly.

13 cl, 13 dwg