| 摘要 |
A device/machine, such as a gas turbine engine, turbocharger, combustion chamber, secondary combustion chamber or a rocket, comprises a wall 22 (which may form part of a turbine guide vane platform 21) having a first surface 22a facing a first space 25 adapted to contain a hot fluid, a second surface 22b to be cooled, a fluid supply chamber 30, which may comprise a chamber 30a supplying fluid to a chamber 30b via a perforated plate, at least one duct 32 for conveying fluid from the chamber 30 to a cavity 31, and a structure, such as a shroud segment 23, comprising a concave deflection surface 34 for directing fluid flow from the duct so it impinges on the surface 22b. The surface may comprise an angled straight portion upstream of a curved portion and a further angled straight portion downstream of the curved portion, details of the surface profile being disclosed. There may be a plurality of ducts, each of which may be parallel to a hot fluid flow direction for inclined, and the dusts may be straight or curved.
|
