| 摘要 |
A gas turbine engine aerofoil 24 has a plurality of attenuation chambers 34 positioned between a cooling air passageway 26 and its leading edge 28. Cooling air passing from the passageway 26 to the exterior surface of the leading edge is attenuated in pressure by impingement on the opposing walls of the respective chambers 34, prior to leaving the chambers 34 via exit passageways 38 which straddle the leading edge. A plurality of input passageways 36 are provided for flow from passageway 26 into the chambers 34, and each chamber may have numerically less input passageways 36 than exit passageways 38. In alternative embodiments, passageways (36, fig 5) connect to upper and/or lower ends of each chamber 36 for pressure attenuation resulting from expansion therein. Hot spots due to blockage and effects due to pressure fluctuation are reduced.
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