| 摘要 |
<p>The method comprises forming blanks (3) of titanium-aluminum material, joining the blanks to a blade ring segment by a cohesive connection and then performing heat treatment, and post-processing the blank composite by material processes. The joining step is carried out by laser beam welding, electron-beam welding, high temperature brazing or friction welding, linear friction welding, orbital friction welding or multi-orbital friction welding. The titanium aluminum material is preheated at a brittle ductile transition temperature of the titanium aluminum during the laser beam welding. The method comprises forming blanks (3) of titanium-aluminum material, joining the blanks to a blade ring segment by a cohesive connection and then performing heat treatment, and post-processing the blank composite by material processes. The joining step is carried out by laser beam welding, electron-beam welding, high temperature brazing or friction welding, linear friction welding, orbital friction welding or multi-orbital friction welding. The titanium aluminum material is preheated at a brittle ductile transition temperature of the titanium aluminum during the laser or electron beam welding. The method further comprises soldering titanium-nickel base by inductive heating. The blanks are formed as a cube, a cuboid with protruding joint zones or as final contour components. An independent claim is included for a blade ring segment for a gas turbine.</p> |
