| 摘要 |
A component such as a turbine blade of a gas turbine engine has a cooling arrangement comprising a cascade impingement array in which cooling air flows from a supply chamber 8 through impingement passages 38, 40 in webs 32, 34 to an internal passageway 14 comprising first and second limbs 16, 18. The cooling air flow through the limbs 16, 18, provides improved heat transfer compared with continued impingement cooling in the chordwise direction of the blade. |
