FIELD: engine technology.
SUBSTANCE: invention relates to the gas turbine engine suspension unit (7). The gas turbine engine suspension unit (7) contains a beam (10) made with the possibility of mounting on the pylon of the aircraft, and a cylindrical part (15) pivotally connected to the ball joint unit. The ball joint unit contains a housing (11) and a ball joint core pivotally connected to the housing (11). The cylindrical part (15) is installed with the possibility of rotation around its axis in the ball joint core. The cylindrical part (15) is made with the possibility of a fixed connection with the fixed part (8) of the gas turbine engine, while the housing (11) of the ball joint unit is fixed to the beam (10).
EFFECT: increase in the degree of double-circuit of the engine is achieved.
10 cl, 5 dwg
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