Method for repairing wear marks on a rotor supporting the fan of a bypass engine
View Patent ↗A method for repairing a flange of a rotor, to a transverse surface of which a disk of a fan in an upstream turbo-fan engine is attached. The flange includes, in a form of a ring, openings for connecting to the disk and intermediate discharge openings. Wear marks are formed by friction of the fan blades on the flange. The method includes machining spot facings onto the flange, in areas with wear marks; placing anti-wear slugs in the discharge openings that can be covered by the blades during friction; and the spot facings extend between the connection openings and are circumferentially limited by clamping surfaces of the connection between the disk and the flange.
1. A method for repairing a flange of a rotor on a transverse face of which there is attached a disk of a fan in an engine having an upstream turbofan, the flange including a ring shape, first openings to connect to the disk, and, between the first openings, stress-relief openings, wear marks being formed by fan blades rubbing on the flange, the method comprising:
machining spot faces on the flange in regions having the wear marks; and
putting in place anti-wear pegs, in the stress-relief openings which are to be at least partially covered by the fan blades during rubbing of the fan blades on the flange,
wherein the spot faces extend between the first openings, and at least one of the spot faces provides a gap in a circumferential direction between a periphery of one of the anti-wear pegs and a border of at least one clamping surface of connection between the disk and the flange.
2. The method as claimed in claim 1 , wherein each spot face between two of the first openings is defined by two radially oriented borders, and at least one of the borders is outside the stress-relief openings.
3. The method as claimed in claim 2 , wherein a depth of the spot face is determined to obtain a sufficient spot facing base radius along the borders to avoid stress concentrations along the borders while limiting a reduction in effective cross section of the flange in a spot facing region.
4. The method as claimed in claim 2 , wherein the flange comprises radial scallops to receive axial hooks of the fan blades, according to which the radial borders extend radially as far as a base of the scallops.
5. The method as claimed in claim 4 , wherein the base of the scallops includes a chamfer, according to which a depth of the spot face is limited such that the depth is less than that of the chamfer.
6. The method as claimed in claim 1 , wherein at least one of the anti-wear ms includes a stem and a collar, and is arranged by sliding assembly in one of the stress-relief openings which is at least partially covered by one of the fan blades, the at least one of the anti-wear pegs being made of metal.
7. The method as claimed in claim 6 , wherein the sliding assembly is created by shrink-fitting the stem of the at least one of the anti-wear pegs in the one of the stress-relief openings.
8. The method as claimed in claim 7 , wherein a surface of the flange has undergone shot peening, and heating of the flange is carried out for a predetermined period and up to a predetermined temperature such that the surface of the flange does not relieve residual stresses from the shot peening.
9. The method as claimed in claim 6 , wherein the stem of the at least one of the anti-wear pegs is deformable in a radial direction, and a plug to radially stretch the stem is arranged on a side opposite the collar.
10. The method as claimed in claim 6 , wherein the stem of the at least one of the anti-wear pegs is deformable in a radial direction, and the stem is pinched such that the stem is insertable into the one of the stress-relief openings, after which the pinching is released.
11. A method for repairing a flange of a rotor on a transverse face of which there is attached a disk of a fan in an engine having an upstream turbofan, the flange including a ring shape, first openings to connect to the disk, and, between the first openings, stress-relief openings, wear marks being formed by fan blades rubbing on the flange, the method comprising:
machining spot faces on the flange in regions having the wear marks; and
putting in place anti-wear pegs, in the stress-relief openings which are to be at least partially covered by the fan blades during rubbing of the fan blades on the flange,
wherein the spot faces extend between the first openings, and the spot faces are bounded in a circumferential direction by clamping surfaces of connection between the disk and the flange, and
wherein each spot face between two of the first openings is defined by two radially oriented borders, and at least one of the borders is outside the stress-relief openings.
12. A method for repairing a flange of a rotor on a transverse face of which there is attached a disk of a fan in an engine having an upstream turbofan, the flange including a ring shape, first openings to connect to the disk, and, between the first openings, stress-relief openings, wear marks being formed by fan blades rubbing on the flange, the method comprising:
machining spot faces on the flange in regions having the wear marks; and
putting in place anti-wear pegs, in the stress-relief openings which are to be at least partially covered by the fan blades during rubbing of the fan blades on the flange,
wherein the spot faces extend between the first openings, and the spot faces are bounded in a circumferential direction by clamping surfaces of connection between the disk and the flange,
wherein at least one of the anti-wear pegs includes a stem and a collar, and is arranged by sliding assembly in one of the stress-relief openings which is at least partially covered by one of the fan blades, the at least one of the anti-wear pegs being made of metal, and
wherein the sliding assembly is created by shrink-fitting the stem of the at least one of the anti-wear pegs in the one of the stress-relief openings.