FIELD: aircraft industry.
SUBSTANCE: invention can be used in control systems of aircraft gas-turbine engines to reveal and prevent surge of compressor. According to proposed method air temperature at compressor input after first group of stages and after compressor is measured, and air pressure after first group of compressor stages and after compressor is measured also. Device contains air temperature transmitter at compressor inlet and the following devices series-connected with said transmitter: first divider and first threshold device, air pressure transmitter after compressor and series connected second divider, and air temperature transmitter after compressor and AND circuit, air temperature transmitter after first group of compressor stages and series-connected first functional converter, third divider, third threshold device, air temperature transmitter after first group of compressor stages, first functional converter, third divider, third threshold device, second functional converter and fourth divider, fourth threshold device, air pressure transmitter after first group of compressor stages.
EFFECT: improved surge protection of compressor.
3 cl, 1 dwg
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Authors
Dates
2005-06-20—Published
2003-12-30—Filed