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US 12,637,982 B2Granted
Modularity of an aircraft turbomachine
AssigneeSafran Aircraft Engines
InventorsPaul Ghislain Albert Levisse, Olivier Belmonte
Life of this patent
Estimating the term…
Abstract
An aircraft turbomachine, including a first shaft having external splines oriented parallel to an axis of rotation of the shaft, a second shaft having internal splines complementary to the external splines, this second shaft being fitted axially on the first shaft and these shafts rotating as one by engagement of their splines, and a system for axially locking the shafts with respect to one another, wherein the system includes screws that are oriented radially with respect to the axis, each of these screws being screwed into a first orifice in one of the shafts and having a free end for engaging a second orifice in the other of the shafts.
Claims13
A set of shafts for an aircraft turbomachine, the set comprising:
- a first shaft comprising external splines oriented parallel to an axis (A) of rotation of the first shaft,
- a second shaft comprising internal splines complementary to said external splines of the first shaft, the second shaft being axially engaged with the first shaft and the first shaft and the second shaft rotating as one by engagement of the external splines and the internal splines, and
- a system for axially locking the first shaft and the second shaft with respect to one another,
- wherein said system comprises screws which are oriented radially with respect to said axis, each of said screws being screwed into a first orifice of one of the first shaft or the second shaft and each of said screws comprises a free end capable of being engaged in a corresponding second orifice of the other of the first shaft or the second shaft, each of said screws being movable by screwing from a first radial position in which said free end is engaged in the second orifice and ensures axial locking of the first shaft and the second shaft, and a second radial position in which said free end is disengaged from said second orifice and ensures axial unlocking of the first shaft and the second shaft, and
- wherein a ring is crimped into each of said second orifices of the other of the first shaft or the second shaft, and is able to receive said free end of each of said screws when each of said screws is in the first radial position.
2 more elements
A set of shafts for an aircraft turbomachine, the set comprising:
- a first shaft comprising external splines oriented parallel to an axis (A) of rotation of the first shaft,
- a second shaft comprising internal splines complementary to said external splines, the second shaft being axially engaged with the first shaft and the first shaft and the second shaft rotating as one by engagement of the external splines and the internal splines, and
- a system for axially locking the first shaft and the second shaft with respect to one another,
- wherein said system comprises screws which are oriented radially with respect to said axis, each of these screws being screwed into a first orifice of one of the first shaft or the second shaft and each of these screws comprising a free end capable of being engaged in a corresponding second orifice of the other of the first shaft or the second shaft, each of said screws being movable by screwing from a first radial position in which said free end is engaged in the second orifice and ensures axial locking of the first shaft and the second shaft, and a second radial position in which said free end is disengaged from said second orifice and ensures axial unlocking of the first shaft and the second shaft,
- wherein a socket is mounted in each of said first orifices and comprises an internal thread for screwing in the corresponding screw,
- wherein said socket comprises an external annular collar for bearing on the corresponding shaft,
- wherein a retaining shell is mounted inside the first shaft and comprises a first cylindrical rim which extends at least partly opposite said first orifice and said second orifice and which is configured to radially retain the screws when in their respective second radial positions,
- and wherein the external annular collar of said socket is radially interposed between the first shaft and a second cylindrical rim of the retaining shell.
5 more elements
A set of shafts for an aircraft turbomachine, the set comprising:
- a first shaft comprising external splines oriented parallel to an axis (A) of rotation of the first shaft,
- a second shaft comprising internal splines complementary to said external splines, the second shaft being axially engaged with the first shaft and the first shaft and the second shaft rotating as one by engagement of the external splines and the internal splines, and
- a system for axially locking the first shaft and the second shaft with respect to one another,
- wherein said system comprises screws which are oriented radially with respect to said axis, each of these screws being screwed into a first orifice of one of the first shaft or the second shaft and each of these screws comprising a free end capable of being engaged in a corresponding second orifice of the other of the first shaft or the second shaft, each of said screws being movable by screwing from a first radial position in which said free end is engaged in the second orifice and ensures axial locking of the first shaft and the second shaft, and a second radial position in which said free end is disengaged from said second orifice and ensures axial unlocking of the first shaft and the second shaft,
- wherein a retaining shell is mounted inside the first shaft and comprises a first cylindrical rim which extends at least partly opposite said first orifice and said second orifice and which is configured to radially retain the screws when in their respective second radial positions,
- wherein the retaining shell comprises an external cylindrical centering surface configured to cooperate with an internal cylindrical surface of the first shaft, the internal cylindrical surface comprising an annular groove for mounting an annular ring for axially retaining the retaining shell relative to the first shaft.
3 more elements
Dependencies are inferred from the claim text.