Gasket device for the bearing of a turbomachine, comprising two elastic seals

Abstract

A gasket device for a turbomachine bearing, configured to separate an oil enclosure and an air enclosure from the turbomachine, including a segmenting gasket for providing most of tightness of the device and a supporting jacket for holding the segmented gasket. The supporting jacket includes a first groove accommodating a first elastic seal for centering the supporting jacket. The supporting jacket includes a second groove accommodating a second elastic seal for centering the supporting jacket, or aligning the axis of the supporting jacket with the axis of the rotor.

Description

TECHNICAL FIELD[0001]The present invention relates to the field of turbomachines. It relates to a gasket device for a turbomachine bearing, as well as the turbomachine including such a device.[0002]The invention is applicable to any type of terrestrial or aeronautical turbomachines, in particular to aircraft turbomachines such as turbofans and turboprop engines. More preferentially, the invention is applicable to a twin spool axial flow turbofan.STATE OF PRIOR ART[0003]Conventionally, a turbomachine bearing supporting a shaft rotating inside a fixed case includes a balling bearing arranged in an enclosure where the lubrication thereof is ensured. However, any oil migration should be avoided toward some compartments of the turbomachine and the tightness should thus be ensured at the separation between the oil containing bearing enclosure and an air-neighbouring enclosure which must be kept free of oil.[0004]Several solutions have already been offered to that end, using for example ca...

AI Technical Summary

Benefits of technology

[0012]Thus, there is a need for a new assembly of a segmented gasket of a gasket device for a turbomachine bearing, enabling the tightness of the device in use to be improved. There is in particular a need to design an assembly of a segmented gasket which is adapted to existing requirements regarding the choice of the materials of turbomachine components.

Problems solved by technology

However, known assemblies from prior art, such as that described in reference to FIG. 1, for a segmented gasket s are generally incapable of meeting these needs, in particular for applications aimed at by the present invention.

In particular, the tightness can be difficult to achieve in use given that the selected material for the support 14, i.e. generally steel because of tribology stresses, substantially expands half as much as that selected for the case element 24, i.e. generally aluminium for most recent engines.

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