| 摘要 |
This invention relates to a gas turbine (10), comprising: axially adjacent first (214) and second (216) components each having a main gas path facing surface within an engine casing (220), an inter component cavity (212) located between the first and second components on the outboard side of the main gas path (218); an axial restrictor (224) located within the inter component cavity for axially restricting movement of the first or second component relative to either or both of the other of the first and second component or the engine casing, wherein the axial restrictor is radially located in the engine casing or other of the first and second component and includes a radially facing surface; a retaining element, comprising a main body (238) having a circumferential length extending around the gas turbine engine and an axial length which extends between axially adjacent first and second components when in use; and, an obstructing portion (240) located between the radially facing surface of the axial restrictor and an opposing second radial surface of the other of the first or second component or engine casing, so as to restrict the radial movement of the axial restrictor, in use. |
