| 摘要 |
A bimetallic ring (80) for use as a turbine shroud in a gas turbine engine. The bimetallic ring forms a sealing surface as a hot gas flow path boundary in the engine. The ring is comprised of two materials (82,84). The first material (82), a wrought, oxidation resistant metal alloy comprises a first portion, which is the hot gas flow path sealing surface. The second material (84), a low cost low alloy steel, comprises a second portion that may be at least a pair of supporting side plates. A dissimilar weld joint (86) joins the sealing surface to the second portion, the at least pair of supporting side plates. |
