| 摘要 |
PROBLEM TO BE SOLVED: To provide a film cooled combustor liner used for a gas turbine engine, in which hot spots are not likely to develop. SOLUTION: A combustor liner (12 or 14) for use in a gas turbine engine includes a first annular panel section (42) having a forward end, an aft end and a first cooling nugget (48) located at the forward end thereof, and a second annular panel section (43) having a forward end, an aft end and a second cooling nugget (56) located at the forward end thereof. The second panel section (43) is joined at its forward end to the aft end of the first panel section. A first row of cooling holes (54) is located in the first cooling nugget, and a second row of cooling holes (62) is located in the second cooling nugget. The dilution holes (84) are located at the aft end of the first panel section immediately upstream of the second cooling nugget.
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