| 摘要 |
PURPOSE:To effectively cool a gas turbine shroud with a minimum supply flow rate of cooling air by entirely sealing a cavity by means of a box-like impinge cover sealedly fixed to a static member composing a casing. CONSTITUTION:A shroud segment 4 which is located on an outer circumference of a turbine moving blade 6 and forms a gas passage therebetween is installed on an outside static member 10 composing a turbine casing. A box-like and porous impinge cover 9, covering an opening of a cavity 3, is sealedly fixed to the outside static member 10. Since the cavity 3 is thus sealed entirely by the impinge cover 9, cooling air is prevented from leaking to the other part, and blown to the shroud segment 4 through a plurality of holes of the impinge cover 9. The maximum cooling effect is obtained with a minimum flow rate of the cooling air. |
