A method for fitting a turbomachine bucket to a turbomachine , the turbomachine comprising a discourager extending from a turbomachine frame in a direction of an axis of rotation of the turbomachine, the method comprising providing the turbomachine bucket, wherein the turbomachine bucket comprises an airfoil and a shank coupled to the airfoil, the bucket comprising an angel wing coupled to the shank by a base portion , wherein the angle wing and the discourager are configured to seal with each other when the turbomachine bucket is installed in the turbomachine , wherein the angle wing is an initial angel wing comprising an axially extending tip extending in a direction (A) of an axis of rotation of the turbomachine bucket and having an initial axial extent sized to accommodate sealing with a number of differently sized discouragers , each differently sized discourager having a different extent in the direction of the axis of rotation of the turbomachine, wherein the discourager of the turbomachine is a particular discourager of the plurality of discouragers , the particular discourager having a particular axial extent , characterized in that the method further comprises modifying the angel wing by removing material from the initial, axially extending tip thereby modifying the axial extent of the axially extending tip to provide a modified angel wing having a modified axially extending tip with a modified axial extent to accommodate the particular discourager having the particular axial extent , wherein the axial extent of the particular discourager is different from a discourager axial extent for which the angel wing was sized prior to the modifying, the method further comprising installing the turbomachine bucket comprising the modified angel wing in the turbomachine frame of the turbomachine having the particular discourager , such that the modified angel wing and the particular discourager axially overlap, but do not touch each other, to restrict a gas flow during operation of the turbomachine. the method comprising providing the turbomachine bucket, wherein the turbomachine bucket comprises an airfoil and a shank coupled to the airfoil, the bucket comprising an angel wing coupled to the shank by a base portion , wherein the angle wing and the discourager are configured to seal with each other when the turbomachine bucket is installed in the turbomachine , wherein the angle wing is an initial angel wing comprising an axially extending tip extending in a direction (A) of an axis of rotation of the turbomachine bucket and having an initial axial extent sized to accommodate sealing with a number of differently sized discouragers , each differently sized discourager having a different extent in the direction of the axis of rotation of the turbomachine, wherein the discourager of the turbomachine is a particular discourager of the plurality of discouragers , the particular discourager having a particular axial extent , characterized in that the method further comprises modifying the angel wing by removing material from the initial, axially extending tip thereby modifying the axial extent of the axially extending tip to provide a modified angel wing having a modified axially extending tip with a modified axial extent to accommodate the particular discourager having the particular axial extent , wherein the axial extent of the particular discourager is different from a discourager axial extent for which the angel wing was sized prior to the modifying, the method further comprising installing the turbomachine bucket comprising the modified angel wing in the turbomachine frame of the turbomachine having the particular discourager , such that the modified angel wing and the particular discourager axially overlap, but do not touch each other, to restrict a gas flow during operation of the turbomachine. <EOS>