Turbine engine fan comprising a balancing system with blind holes for accommodating masses
View Patent ↗A fan for an aircraft turbine engine, including an intake cone including a balancing system including a plurality of mass accommodation holes and at least one balancing mass mounted in one of the holes. The balancing system further includes an attachment mechanism exerting pressure that flattens the balancing mass against the bottom of its mass accommodation hole, the accommodation hole being made blind in the intake cone, so as to open out inside the intake cone.
1. A fan for an aircraft turbine engine, comprising:
a turbine engine intake cone including an outer surface configured to be followed by a vein of the turbine engine;
a fan disk and fan blades mounted on the disk with which the fan blades rotate about an axis of rotation of the fan;
a balancing system rotationally coupled with the fan disk about the axis of rotation, the balancing system including:
a plurality of mass accommodation holes spaced apart circumferentially from each other,
at least one balancing mass mounted in one of the accommodation holes, and
attachment means exerting pressure flattening the balancing mass against the bottom of its mass accommodation hole, the accommodation hole being made blind in the intake cone, so as to open out inside the intake cone,
wherein the mass accommodation holes are formed in an inner surface of the intake cone such that the mass accommodation holes are concealed from the vein.
2. The fan according to claim 1 , wherein the attachment means and the balancing mass cooperate to form a balancing mass assembly.
3. The fan according to claim 2 , wherein the attachment means comprises a part forming a nut and a pressure screw screwed into the part, the nut being retained to the cone in the direction of the pressure screw.
4. A fan for an aircraft turbine engine, comprising:
a turbine engine intake cone including an outer surface configured to be followed by a vein of the turbine engine;
a fan disk and fan blades mounted on the disk with which the fan blades rotate about an axis of rotation of the fan;
a balancing system rotationally coupled with the fan disk about the axis of rotation, the balancing system including:
a plurality of mass accommodation holes spaced apart circumferentially from each other,
at least one balancing mass mounted in one of the accommodation holes, and
attachment means exerting pressure flattening the balancing mass against the bottom of its mass accommodation hole, the accommodation hole being made blind in the intake cone, so as to open out inside the intake cone,
wherein the mass accommodation holes open out in a bottom of a groove centered on the axis of rotation, and the groove on either side of its bottom respectively includes two sidewalls formed so as to form the part of the attachment means retaining a nut in the groove.
5. The fan according to claim 4 , wherein the groove opens radially inwards.
6. A fan for an aircraft turbine engine, comprising:
a turbine engine intake cone including an outer surface configured to be followed by a vein of the turbine engine;
a fan disk and fan blades mounted on the disk with which the fan blades rotate about an axis of rotation of the fan;
a balancing system rotationally coupled with the fan disk about the axis of rotation, the balancing system including:
a plurality of mass accommodation holes spaced apart circumferentially from each other,
at least one balancing mass mounted in one of the accommodation holes, and
attachment means exerting pressure flattening the balancing mass against the bottom of its mass accommodation hole, the accommodation hole being made blind in the intake cone, so as to open out inside the intake cone,
wherein the balancing mass includes an end with a spherical portion shape, mating a shape of the bottom of the accommodation hole against which the balancing mass is flattened.
7. The fan according to claim 1 , wherein the cone comprises aluminum.
8. The fan according to claim 1 , wherein the intake cone is made from an upstream portion fixedly mounted on a downstream portion forming a shroud, and the balancing system is implanted on the downstream portion forming the shroud.
9. The fan according to claim 1 , wherein during operation, at least one of the mass accommodation holes is left free.
10. The fan according to claim 1 , wherein the intake cone includes an annular attachment flange fixedly added onto the fan disk.
11. The fan according to claim 1 , further comprising a ring for retaining the fan blades with which the fan blades may be retained axially relatively to the fan disk, the retaining ring being rotationally coupled with the fan disk.
12. The fan according to claim 1 , wherein the intake cone extends downstream as far as the fan blades.
13. A turbine engine for an aircraft comprising a fan according to claim 1 .
14. The turbine engine for an aircraft according to claim 13 , which is a jet turbine engine.