| 摘要 |
A control system actively controls at least one troublesome mode of an unsteady motion phenomenon in turbomachinery in order to enable an increase in the operating range of the turbomachinery. For example, rotor blade flutter or rotating stall may be controlled in a turbocompressor. Surge, forced vibration and acoustic resonance may also be controlled. The control system has a control bandwidth which is at least partly coextensive with the bandwidth of the unsteady motion phenomenon and operates by passing sensor signals related to the unsteady motion phenomenon from a sensor array in the turbomachine to a mode selector/filter which selects those sensor signal components which are related to the troublesome mode. The selected mode signals are amplified and phase-shifted by time-variable amounts so as to produce control signals having controlled amplitude and phase relationship to the troublesome mode. Actuators in an actuator array are continuously driven by the control signals and produce physical effects in the turbomachine which act counter to the troublesome mode without exciting others. Various kinds of actuator for an aircraft gas turbine engine are disclosed, including adjustable vanes and blades, loudspeakers, modulated flow injectors, heat injectors, variable bleed valves, blade shakers and fuel flow modulators.
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