| 摘要 |
A closed-loop control system for a gas turbine, in particular an aircraft engine, has devices for blade-tip blowing-in (ASC) in order to improve the compressor stability, which devices are activated when required. The closed-loop control system is characterized in that it has devices for active gap control (ACC), preferably in the high-pressure compressor, by which means the radial gap in the high-pressure compressor is kept in an optimum operating range, and wherein the control system has a common engine regulator (1) for both devices (ASC, ACC). The invention avoids the technical problems of the prior art and provides a better closed-loop control system for a gas turbine, in particular an aircraft engine, for active stabilization of the compressor. |
