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US 8,985,952 B2Granted
Turbine engine fan comprising a balancing system with blind holes for accommodating masses
AssigneeSnecma
InventorsOlivier Belmonte, Lionel Rene Henri Weller
Life of this patent
Estimating the term…
Abstract
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.
Claims14
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.
4 more elements
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.
4 more elements
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.
4 more elements
Dependencies are inferred from the claim text.