METHOD OF GAS TURBINE ENGINE PROTECTION Russian patent published in 2013 - IPC F04D27/02 

FIELD: engines and pumps.

SUBSTANCE: air pressure downstream of compressor is measured at all operating conditions to calculate relative variation and relative air pressure variation rate behind the compressor. Relative pressure variation is compared with first preset magnitude defined for every gas turbine engine experimentally. Relative pressure variation rate is compared with second preset magnitude defined for every gas turbine engine experimentally. In case relative pressure variation exceeds said first preset magnitude and relative variation rate exceeds second preset magnitude, signal "SURGE" is generated to stop fuel feed in combustion chamber for preset time defined for every engine in acceptance tests. Valve to bypass air from intermediate sections of engine compressor and from behind the compressor is opened to cut on ignition switch for preset time. In case relative pressure rate falls below first preset magnitude and relative pressure variation is lower than second preset magnitude, signal "SURGE" is removed to control gas turbine engine in compliance with standard control programs.

EFFECT: higher quality of automatic control system, reliability of engine and aircraft safety.

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