| 摘要 |
A cooled gas turbine engine component comprises a wall (40) having a first and second surfaces (41, 43). The second surface (43) has a plurality of recesses (58) and each recess (58) has a planar upstream end surface (64) arranged so that it hangs over the upstream end (60) of the recess (58). Each recess (58) has a depth (D) equal to the required depth (D R ) plus the thickness (T) of the thermal barrier coating (74) to be deposited. The wall (40) has a plurality of angled (± 1 ) effusion cooling apertures (50) extending from the first surface (41) towards the second surface (43). Each effusion cooling aperture (50) has an inlet (52) in the first surface (41) and an outlet (54) in the end surface (64) of a corresponding one of the recesses (58) in the second surface (43). Each recess (58) has smoothly curved transitions (65, 70, 72) from the end surface (64) and side surfaces (66, 68) to the second surface (43). Blocking of the effusion cooling apertures (50) by thermal barrier coating (74) is reduced. |
