Breakable coupling system for a turbojet fan shaft
View Patent ↗The invention relates to a rotary shaft arrangement carrying equipment at one end and extending rearwards from the equipment, the shaft ( 1 ) being supported by a first bearing ( 2 ) behind the equipment, and by a second bearing ( 3 ) behind the first bearing ( 2 ), the first bearing ( 2 ) being carried by a casing ( 4 ) surrounding the shaft ( 1 ) and extending rearwards from the first bearing ( 2 ) to a stator structure ( 5 ) to which the casing ( 4 ) is fastened by screws ( 6 ) that extend parallel to the shaft ( 1 ) and that are fusible in traction, the arrangement being characterized by the fact that the second bearing ( 3 ) is disposed with radial clearance (J) in a bore ( 7 ) of an annular support ( 8 ) secured to the stator structure ( 5 ), and is fastened to said annular support ( 8 ) by screws ( 9 ) that are parallel to the shaft ( 1 ) and that are fusible in shear, whereby the second bearing ( 3 ) can bear against said support ( 8 ) in the event of said screws ( 9 ) rupturing. The invention relates more particularly to the support for the fan shaft of a turbojet.
1. A rotary shaft arrangement carrying equipment at one end and extending rearwards from the equipment, the shaft being supported by a first bearing behind the equipment, and by a second bearing behind the first bearing, the first bearing being carried by a casing surrounding the shaft and extending rearwards from the first bearing to a stator structure to which the casing is fastened by screws that extend parallel to the shaft and that are fusible in traction,
wherein the second bearing is disposed with radial clearance in a bore of an annular support secured to the stator structure, and is fastened to said annular support by screws that are parallel to the shaft and that are fusible in shear, whereby the second bearing can bear against said support in the even of said screws rupturing.
2. An arrangement according to claim 1 , wherein the radial clearance is calibrated so as to avoid friction between the shaft and other elements, whether stationary or moving.
3. An arrangement according to claim 2 , wherein the radial clearance is no more than 3 mm.
4. An arrangement according to any one of claims 1 to 3 , wherein the equipment is an entry fan of a turbojet.
5. An arrangement according to claim 1 , wherein the second bearing includes an outer ring which presents an outwardly-directed radial annular flange that is pressed against a side face of the annular support by the fusible screws.
6. An arrangement according to claim 5 , wherein the outer ring is maintained centered in the bore of the annular support by a plurality of studs extending parallel to the shaft said studs being calibrated to shear in the event of the second bearing becoming uncoupled.
7. An arrangement according to claim 6 , wherein the studs are provided on the annular support and extend from the periphery of the flange.
8. An arrangement according to claim 7 , wherein the annular support has three studs that are regularly distributed around the axis of the bore.
9. An arrangement according to claim 5 , further comprising means for preventing the outer ring from turning in the event of the second bearing becoming uncoupled.
10. An arrangement according to claim 9 , wherein the means for preventing the outer ring from turning in the event of uncoupling comprise at least one pin anchored in the annular support passing with clearance through an orifice formed in the flange.
11. An arrangement according to claim 10 , wherein the pin includes a pin head bearing against an outside face of the flange so as to prevent the second bearing from moving axially in the event of the second bearing becoming uncoupled.
12. An arrangement according to claim 10 , comprising three pins that are regularly distributed around the axis of the bore.
13. A turbojet comprising an arrangement according to claim 1 .