GAS-DYNAMIC SEAL OF GAS TURBINE ENGINE ROTOR SUPPORT Russian patent published in 2020 - IPC F16J15/16 F04D29/10 

FIELD: engine building.

SUBSTANCE: invention relates to aircraft engineering, specifically to seals of oil cavities of supports of rotors of gas turbine engines and power plants. Gas-dynamic seal of gas turbine engine rotor support includes contact seal arranged between pre-oil and air and oil cavities of rotor support. Contact seal contains a sealing element installed with the possibility of interaction with the housing and pressed by springs to the rotating bushing fixed on the rotor, and equipped with a magnetic ring with a lock nut. Sealing element is made in the form of parking inertial seal and impeller seal formed by annular protrusion on housing and annular ledge on bushing with blades on side of protrusion on housing, installed with formation of compensating channel between them, which is connected to oil cavity. Magnetic ring with a lock nut is installed on the body to form a radial flow channel connected to the compensation channel and the oil cavity. Parking inertial seal is made in the form of two movable sectional annular floating inserts installed in two-chamber annular frame body, fixed on rotating bushing. One chamber is open in the direction of the housing, and the other one – towards the rotating bushing. One insert is installed with the possibility of interaction with the housing, and the other one – with the possibility of interaction with the rotating bushing. Insert interacting with the rotating bushing is provided with a tightening binding spring; at that, the weight of the insert with tightening shroud spring is larger than the weight of the insert installed with the possibility of interaction with the case. Said inserts are articulated on annular casing central wall by adjacent swinging levers to transmit centrifugal force acting on paired annular inserts, providing inertial opening of parking inertial seal and connection of pre-oil – air cavity with compensation channel of impeller seal at preset rotor speed of gas turbine engine.

EFFECT: invention allows improving reliability of gas turbine engine operation and expansion of its operational capabilities.

4 cl, 1 dwg