Turbomachine with axial force adjustment at a bearing
AssigneeSafran Aircraft Engines
InventorFrancois Gallet
Life of this patent
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Abstract
A turbomachine including a stator, a rotor mounted on a shaft, a first bearing and a second bearing downstream of the first bearing in a direction of air circulation at the inlet of the turbomachine, the first bearing forming an axial abutment linked to the stator, the second bearing including an inner ring secured to the shaft and an outer ring mounted on an arm secured to the stator, the second bearing including rolling elements in axial support on the inner ring and on the outer ring. The outer ring includes a radially extending ring portion. The turbomachine also includes an axial force application device mounted between the arm and the ring portion.
Claims12
A turbomachine including a stator and a rotor mounted on a shaft, the rotor including vanes in a flow path, the rotation of the shaft and the rotor with respect to the stator being ensured by a set of bearings including a first bearing and a second bearing downstream of the first bearing in a direction of air circulation at an inlet of the turbomachine, said first bearing forming an axial abutment linked to the stator on which said shaft exerts, under the effect of the rotation of the vanes, an axial force in a given direction during the main operating phases of the turbomachine,
- the second bearing comprising an inner ring secured to the shaft and an outer ring mounted on an arm secured to the stator, wherein the arm comprises an arm end which is radially located opposite the outer ring and outwardly of the outer ring,
- the turbomachine comprising rolling elements in axial support on the inner ring and on the outer ring,
- and comprising a collar which is axially located at a downstream end of the outer ring and extends radially outwardly from the outer ring,
- wherein the turbomachine further comprises an axial force application device mounted between the arm end and the collar,
- wherein the force application device further comprises a piston and further comprises a pressurized oil supply system at the piston, so as to exert an axial force on the outer ring by oil supply,
- wherein the turbomachine further comprises a liner, wherein the liner partly extends against a downstream face of the arm and partly extends radially outwardly of the piston, a piston chamber being formed between the liner and the piston.
A turbomachine including a stator and a rotor mounted on a shaft, the rotor including vanes in a flow path, the rotation of the shaft and the rotor with respect to the stator being ensured by a set of bearings including a first bearing and a second bearing downstream of the first bearing in a direction of air circulation at an inlet of the turbomachine, said first bearing forming an axial abutment linked to the stator on which said shaft exerts, under the effect of the rotation of the vanes, an axial force in a given direction during the main operating phases of the turbomachine,
- wherein the second bearing comprises a tapered roller bearing which comprises an inner ring secured to the shaft and an outer ring mounted on an arm secured to the stator,
- the tapered roller bearing comprising conical rollers in axial support on the inner ring and on the outer ring,
- wherein the outer ring comprises a radially extending ring portion and the turbomachine comprises an axial force application device mounted between the arm and the ring portion, the axial force application device being configured to take up axial forces exerted on the second bearing by allowing the outer ring to axially move relative to the arm,
- wherein the force application device comprises a piston, and further comprises a pressurized oil supply system at the piston so as to exert an axial force on the outer ring by oil supply,
- wherein the turbomachine further comprises a liner, wherein the liner partly extends against a downstream face of the arm and partly extends radially outwardly of the piston, a piston chamber being formed between the liner and the piston.
Dependencies are inferred from the claim text.