| 摘要 |
<p>A ventilation arrangement for an annular cavity (26) located about the core engine of a gas turbine (10), the annular cavity (26) having an axis (11) and an inner wall (24) located about the axis and an outer wall (25) radially spaced there-from, the outer wall being interposed between the cavity (26) and an engine bypass duct (22). The ventilation arrangement comprises a plurality of ventilation ducts (30,34) passing through said outer wall (25) and providing for fluid communication between the bypass duct (22) and the cavity (26) and a flow diverter (35) arranged at an oblique angle to a radial alignment with said axis (11) so as to induce in the ventilation flow from said ducts a vortical flow component about the inner wall. The ducts (34) may be shaped to provide the flow diverter. The internal geometry of the ducts may provide for a sudden expansion (33) to control the exit profile of the flow into the cavity.</p> |
