| 摘要 |
Where gas turbine engine structure eg combustion equipment, is to be air impingement cooled, the surface which receives the air jets is so shaped as to produce boundary layer separation zones 34, 38 and 44 in the cooling air, as it spreads across the surface. Mixing of the boundary layer with the remainder of the air flow results, followed by the reestablishment of the boundary layer. The new boundary layer is cooler than the original layer and so provides more effective cooling.
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