| 摘要 |
For the sake of improving performance of a gas turbine engine (310), the present disclosure teaches an airfoil (400) for a gas turbine engine, comprising an airfoil body (410) having a leading edge (411), a trailing edge (412) and a cavity (420), and a tubular impingement element (430) having a plurality of impingement openings (433), wherein the impingement element is mounted in the cavity, the leading edge is substantially straight as viewed orthogonally onto a longitudinal axis of the leading edge from at least one direction, a trailing perimeter of the cavity is substantially straight as viewed orthogonally onto a longitudinal axis of the trailing perimeter from at least one direction, and the trailing edge is curved relative to a longitudinal axis of the trailing edge.
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