| 摘要 |
A component, such as a turbine blade for a gas turbine engine, has a cooling arrangement comprising a supply passage 18 within the component from which extend cooling passages 28 of a first array which open at discharge openings 29, for example at a trailing edge of the blade. Cooling passages 30 of a second array extend into the blade from discharge openings 31, and intersect the passages 28. The passages 30 terminate short of the supply passage 18. Some of discharge openings 29, 31 may open on a pressure face of a turbine blade. The first and second arrays may be parallel or inclined to one another. The arrays may be in a curved plane.
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