| 摘要 |
A gas turbine engine component has first and second walls 52 that define a passageway 61 for the flow of a fluid C. The second wall defines at least one impingement hole 70 for the flow of an impingement fluid A. The second wall comprises a deflector wall 80 around at least a part of the impingement hole and extending from the second wall towards the first wall. The deflector wall may extend between 25% and 95%, and preferably 75%, of the distance between the walls. The deflector wall may surround the entire impingement hole, or may surround a portion, preferably at least 90°, of the hole. An inner surface of the deflector wall may be continuous with the impingement hole, or spaced there from. A plurality of impingement holes may be provided, and downstream (relative to fluid flow C) holes may extend further towards the first wall. The component may be an aerofoil (blade) or combustor wall. |
