FIELD: aircraft engineering.
SUBSTANCE: claimed group of inventions includes a transmission shaft, an aircraft gas turbine engine containing the specified transmission shaft, and a method for protecting the gas turbine engine from exceeding the torque of the transmission shaft. The transmission shaft of the aircraft gas turbine engine contains the first and second sections. At the same time, the means for connecting the sections comprise at least one bellows containing the first section and the second sections framing the said first section. The first section contains at least one breaking section, including at least one through hole, and is configured to break when the value of the torque acting on the said first section exceeds a predetermined threshold value.
EFFECT: increase in engine safety is achieved.
14 cl, 9 dwg
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