Oil restrictor for emergency lubrication of a component for an aircraft turbine engine
AssigneeSafran Transmission Systems
InventorsAlexis Claude Michel Dombek, Patrice Jocelyn Francis Gedin
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Abstract
An oil restrictor for emergency lubrication of a component for an aircraft turbine engine includes a metal cylindrical body having a longitudinal axis and configured to be housed in and shrink-fitted into a cylindrical bore of a part of the turbine engine. The restrictor further includes an integrated oil circuit enabling oil to pass through the restrictor along the axial extent thereof. The body is a one-piece body, and the circuit has at least two oil channels recessed on an outer cylindrical surface of the body and extending around and/or along the axis.
Claims13
An oil restrictor for the emergency lubrication of a component for an aircraft turbine engine, the restrictor comprising a cylindrical body extending along a longitudinal axis and configured to be housed and shrink-fitted in a cylindrical bore of a part of the turbine engine, the restrictor further comprising an integrated oil circuit configured to provide passage of oil through the restrictor along an axial extent of the restrictor, wherein the body is a one-piece body, and the integrated oil circuit comprises at least two oil channels recessed on a single outer cylindrical surface of the body and extending around and/or along said axis, and wherein said at least two oil channels are independent from each other and remote from each other so as not to communicate directly with one another.
An oil restrictor for the emergency lubrication of a component for an aircraft turbine engine, the restrictor comprising a cylindrical body extending along a longitudinal axis and configured to be housed and shrink-fitted in a cylindrical bore of a part of the turbine engine, the restrictor further comprising an integrated oil circuit configured to provide passage of oil through the restrictor along an axial extent of the restrictor, wherein the body is a one-piece body, and the integrated oil circuit comprises at least two oil channels recessed on an outer cylindrical surface of the body and extending around and/or along said axis,
- wherein the body comprises first and second opposite longitudinal ends each provided with a longitudinal end face radial to the longitudinal axis, each of the oil channels comprising a first channel end opening at the first longitudinal end of the body and an opposite second channel end in fluid communication with a duct of the body, the duct having a radial orientation with respect to said longitudinal axis and extending between said second channel end and a blind hole formed in a center of the radial face of the second longitudinal end of the body.
Dependencies are inferred from the claim text.