FIELD: aviation.
SUBSTANCE: invention relates to the resilient damping support of turbine of gas turbine engines for aviation and ground usage. Resilient damping support of turbine, comprising a support body with internal and external elastic elements with a slotted oil cavity between them, and also separating oil and air cavities of the shell, outer surface of the support body is cylindrical with the telescopic axially installed inner shell flange with a sealing element in the annular recess, and the slotted oil cavity is connected by uniformly circumferential channels with annular grooves of the oil supply in the two radial planes.
EFFECT: invention makes it possible to avoid the appearance of bending stresses in the separation shell due to various temperature deformations of the structural support elements, to increase the robustness of the resilient damping support, to provide uniform oil supply in the axial and radial directions to the slotted oil cavity, and also to provide specified damping properties of the support.
1 cl, 2 dwg
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