| 摘要 |
An engine component (90, 190) for a gas turbine engine (10) includes a film-cooled recess comprising a contoured portion (112, 212) defining a step (116, 216). A hot surface (94, 194) facing hot combustion gas (H) and a cooling surface (96, 196) facing a cooling fluid flow (C) are fluidly coupled by a passage (106, 206) through the engine component (90, 190). The passage (106, 206) further comprises an inlet (102, 202) in the cooling surface (96, 196) and an outlet (104, 204) in the step (116, 216). The inlet (102, 202), passage (106, 206), and outlet (104, 204) are oriented such that the cooling fluid (C) flowing through the passage (106, 206) and exiting the outlet (104, 204) diffuses within the contoured portion (112, 212) preventing premature mixing out with the hot fluid flow (H). |
