| 摘要 |
The invention relates to a film-cooled gas turbine component (8) for a gas turbine, comprising a surface (38) which can be exposed to a hot gas (39) and in which a number of film-cooling openings (36) end, wherein each of the film-cooling openings (36) in question comprises, along the flow-through direction thereof, a channel segment (48) and a diffuser segment (46), which directly adjoins the channel segment and which comprises a diffuser edge (44) arranged upstream, two longitudinal edges (42), and a diffuser edge (40) arranged downstream, wherein each longitudinal edge (42) meets the diffuser edge (44) arranged downstream in a corner region (54). In order to provide an effective arrangement of film-cooling openings (36), the cooling film of which arrangement is closed more closely after the diffuser edge arranged downstream than previously, according to the invention, at least two directly adjacent, preferably all film-cooling openings (36) of the row (30, 34) are designed in such a way that the channel axes (50) of the respective channel segments (48) of the film-cooling openings are angled from the local flow direction (52) of the hot gas (39) and the diffuser segments (46) of the film-cooling openings are each asymmetric in such a way that the directly adjacent corner regions (54) of the film-cooling openings (36) in question are aligned as viewed in the flow direction (52) of the hot gas (39). |
