| 摘要 |
Surge conditions in the compressor of a gas turbine aeroengine can be automatically controlled by a surge control system in which compressor outlet pressure is monitored and a signal P corresponding to it is processed in a surge detector to determine the ratio P/P and to compare the value of the ratio with a predetermined reference value, surge correction control signals being outputted whenever a surge is detected. Surge is controlled as these signals actuate various units linked with the surge detector, these units achieving bleeding off of air from the compressor, reduction of the mass flow of fuel to the aeroengine, and maintenance of fuel ignition for a predetermined period.
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