| 摘要 |
<p>A multistage compressor for a gas turbine, having a compressor housing, guide vanes, impeller vanes, a hub area, discharge ports, and injection ports for stabilizing the compressor flow, wherein the discharge ports are situated at least one stage downstream from the injection ports, the injection ports being fashioned as nozzles, and the geometry of these nozzles is designed such that the flow speed of the injected air stream is significantly greater than the speed of the flow in a critical cross-section.</p> |
