Method for intentionally mistuning a turbine blade of a turbomachine
The present invention relates to a method ( 100 ) for intentionally mistuning a turbine blade of a turbomachine ( 10 ), by providing raised portions ( 31 ) or slots ( 32 ), the position of which is calculated on the basis of a vibration analysis of the disk (steps a) to d)).
1. A method for intentionally mistuning a bladed wheel of a turbomachine, said bladed wheel comprising a disc extending around a longitudinal axis and N blades distributed uniformly around said longitudinal axis and extending radially relative to this axis from the disc, N being a nonzero natural integer, said method comprising the following steps:
a) selecting a natural vibration mode of the bladed wheel with k nodal diameters, k being a natural integer different to zero and, when N is an even number, different to
N
2
,
said natural mode being a vibration mode in the operating range of the turbomachine;
b) determining a displacement of the blades over an entire circumference of the bladed wheel for each of two standing deformation waves of the same frequency which are combine to generate a rotating mode shape of the bladed wheel in the selected natural vibration mode;
c) from the displacement of the blades thus determined for each of the two standing deformation waves, determining the blades for which a vibration antinode of a first of said standing deformation waves corresponds to a vibration node of the second standing deformation wave;
d) providing a projection or a notch in the disc of the bladed wheel facing each of the blades thus determined, so as to frequentially separate the two standing deformation waves and intentionally mistune the bladed wheel relative to the selected natural vibration mode.
2. The method according to claim 1 , wherein the notches are made by counterboring or the projections are made by metallization.
3. The method according to claim 1 , wherein the disc comprises an annular platform from which the blades extend radially, the projections or the notches being provided in said platform of the disc.
4. The method according to claim 1 , wherein the projections or the notches are provided in the disc so as to extend over an angular amplitude around the longitudinal axis of between 360°/N and 80°.
5. A bladed wheel of a turbomachine comprising a disc extending around a longitudinal axis and N blades distributed uniformly around said longitudinal axis and extending radially from the disc, N being a nonzero natural integer, said bladed wheel being characterized in that it comprises a plurality of projections or notches provided in the disc facing each of the blades determined according to steps a) to c) of the method for intentionally mistuning a bladed wheel of a turbomachine according to claim 1 .
6. The bladed wheel according to claim 5 , wherein the notches are made by counterboring or the projections are made by metallization.
7. The bladed wheel according to claim 5 , wherein the disc comprises an annular platform from which the blades extend radially, the projections or the notches being provided in said platform of the disc.
8. The bladed wheel according to claim 5 , wherein the projections or the notches are provided in the disc so as to extend over an angular amplitude around the longitudinal axis of between 360°/N and 80°.