FIELD: aviation.
SUBSTANCE: invention relates to a gas turbine engine of an aircraft. The gas turbine engine contains a high pressure cascade, front case (14), and suspension means (12, 13) of the gas turbine engine, made with the possibility of attachment of the gas turbine engine to pylon (11) of the aircraft. Suspension means (12, 13) contain front suspension assembly (12), rear suspension assembly (13). Front suspension assembly (12) contains beam (16), at least two connecting thrusts, a traverse pivotally connected to beam (16) at a level of an area of the specified traverse, central in a circumferential direction, at least two thrusts (19) of traction force perception. Rear suspension assembly (13) is made with the possibility of connection of pylon (11) to stationary rear case (15) of the gas turbine engine.
EFFECT: increase in a degree of double-circuit of a gas turbine engine.
10 cl, 5 dwg
| Title | Year | Author | Number |
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|
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