FIELD: aviation.
SUBSTANCE: invention relates to aircraft engine building, particularly, to gas turbine engine rotor support assemblies. Problem of increasing gas-dynamic efficiency of compressor due to provision of stable optimum values of radial clearances between rotor blades and compressor stator is solved by the fact that in front support of compressor rotor including radial-thrust ball bearing 1, installed by its outer casing 2 in housing of bearing 3 of housing of front support 4 with thin-walled conical diaphragm 5 and flange 6 fixed to intermediate housing of engine 7, housing of front support 4 is equipped with coaxial coupling sleeve in form of thin-walled conical diaphragm 8, fixed to housing of bearing 3 and to intermediate housing of engine 7 with provision of compressive force in thin support wall cone diaphragm 5 of front support.
EFFECT: thus increasing bending stiffness of conical diaphragm of compressor rotor front support housing due to its preliminary loading with compression force to ensure stable optimum radial clearances between rotor blades and compressor stator provides high level of gas-dynamic efficiency of compressor.
1 cl, 2 dwg
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