FIELD: engines and pumps.
SUBSTANCE: device is designed to detect rotor shaft failure in gas turbine, primarily, of aircraft engine first medium-pressure turbine. Second, low-pressure turbine, is arranged along gas flow and behind the latter and incorporates control element arranged between first turbine rotor and second turbine stator, radially inside flow section of gas turbine, and sensitive element arranged in second turbine stator. Said sensitive element generates electric signal, in response to operation of said control element caused by shaft failure, to be sent to switching element arranged radially outside gas turbine flow section and on turbine housing.
EFFECT: higher reliability of detecting failure of center shaft coupling medium-pressure turbine with medium-pressure compressor.
16 cl, 1 dwg
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