Arrangement of bearing supports for the rotating shaft of an aircraft engine and an aircraft engine fitted with such an arrangement
View Patent ↗An arrangement of bearing supports for a rotating shaft mounted on bearings connected to an engine stator structure by bearing supports of which at least one is made up of N>1 elements effectively acting in parallel to simultaneously connect the bearing to the structure, of which N−1 of the N elements form this connection by fusible links, is made up of a first bearing supported by a first bearing support and a second bearing supported by a second bearing support, that of the two bearing supports which makes up the N>1 elements being the second bearing support.
1. An arrangement of bearing supports for a rotating shaft in an aircraft engine, said rotating shaft having a front portion carrying an equipment and extending in a rear direction from said front portion, said rotating shaft being mounted successively, in said rear direction from said front portion, on a front bearing linked to an engine stator structure by a first of said bearing supports and on a rear bearing linked to said engine stator structure by a second of said bearing supports, wherein the second bearing support comprises N>1 elastic elements which act substantially in parallel to simultaneously form a connection of said rear bearing to said engine stator structure, N−1 of said N elastic elements forming said connection through fusible components,
wherein said second bearing support having N>1 elements further comprises radial end-stop components to restrict the radial displacement of the rotating shaft when the fusible components are broken, and
wherein said second bearing support having N>1 elements further comprises damping components associated with said radial end-stop components.
2. An arrangement of bearing supports according to claim 1 , wherein said rear bearing is an axial end-stop effect bearing.
3. An arrangement of bearing supports according to claim 2 , wherein said rear bearing is a ball bearing.
4. An arrangement of bearing supports according to claim 1 , wherein said front bearing is a roller bearing.
5. An arrangement of bearing supports according to claim 1 , wherein said second bearing support comprises two said elastic elements acting substantially in parallel and simultaneously connecting said rear bearing to said structure, and wherein said two elements have different stiffness and form respectively a stiff element and a flexible element, said stiff element providing said connection between said rear bearing and said structure through said fusible components.
6. An arrangement of bearing supports according to claim 5 , wherein the stiff element has an essentially rectilinear longitudinal section.
7. An arrangement of bearing supports according to claim 6 , wherein the flexible element has a profile forming successively, from the rear bearing, a proximal curve having its concavity opposite to the rear bearing and a distal curve having its concavity opposite to the concavity of the proximal curve, in longitudinal section.
8. An arrangement of bearing supports according to claim 7 , wherein said flexible element comprises axial end-stop components to take up axial forces transmitted by the rear bearing when the fusible components are broken.
9. An arrangement of bearing supports according to claim 5 , wherein said flexible element comprises axial end-stop components to take up axial forces transmitted by the rear bearing when the fusible components are broken.
10. An aircraft engine, comprising an arrangement of bearing supports according to claim 1 .
11. An arrangement of bearing supports for a rotating shaft in an aircraft engine, said rotating shaft having a front portion carrying an equipment and extending in a rear direction from said front portion, said rotating shaft being mounted successively, in said rear direction from said front portion, on a front bearing linked to an engine stator structure by a first of said bearing supports and on a rear bearing linked to said engine stator structure by a second of said bearing supports, wherein the second bearing support comprises N>1 elastic elements which act substantially in parallel to simultaneously form a connection of said rear bearing to said engine stator structure, N−1 of said N elastic elements forming said connection through fusible components,
wherein said second bearing support comprises two said elastic elements acting substantially in parallel and simultaneously connecting said rear bearing to said structure, and wherein said two elements have different stiffness and form respectively a stiff element and a flexible element, said stiff element providing said connection between said rear bearing and said structure through said fusible components, and
wherein the flexible element has a profile forming successively, from the rear bearing, a proximal curve having its concavity opposite to the rear bearing and a distal curve having its concavity opposite to the concavity of the proximal curve, in longitudinal section.