| 摘要 |
<p>An air bleed system for a compressor, particularly for gas turbine engines is provided with an air bleed from a portion of the compressor to an annular chamber through an annular opening in the casing; an annular passage is connected to the opening and terminates in the annular chamber surrounding the casing; a plurality of turning vanes change the direction of flow of the bleed air by 90 DEG to induce a circulating flow of air in the chamber; flush openings and ducts angle circumferentially in the direction of the circulating flow in the annular chambers supply air to the engine and aircraft accessories.</p> |
