The invention relates to a method and a set of balance weights for balancing a rotor, particularly of a turbomachine, on which a plurality of balance weights, which are distributed over the periphery, can be arranged for balancing an imbalance. A set of balance weights, in particular plate-shaped weights, with a predetermined number of groups of balance weights, is used for balancing the rotor. Each of the balance weights of every group of balance weights has an identical weight that is assigned to this group and a shape assigned to this group, which differs in basic shape and/or thickness of the balance weights from the balance weights of the other groups.

The invention relates to a method and a set of balance weights for balancing a rotor, particularly of a turbomachine, on which a plurality of balance weights, which are distributed over the periphery, can be arranged for balancing an imbalance. A set of balance weights, in particular plate-shaped weights, with a predetermined number of groups of balance weights, is used for balancing the rotor. Each of the balance weights of every group of balance weights has an identical weight that is assigned to this group and a shape assigned to this group, which differs in basic shape and/or thickness of the balance weights from the balance weights of the other groups.

A balance ring for a gas turbine engine has a ring shaped body with a first radial thickness, an anti-rotation tab extending outward from the body and at least one millable balancing feature connected to the body.

A weight applicator including a weight applicator head and at least one actuator is disclosed. The weight applicator head is adapted to carry a wheel balance weight and has a weight application surface with a weight retaining region and a leading rotation region. The at least one actuator is coupled to the weight applicator head for manipulating the weight applicator head in at least one direction. The at least one direction has a radial component. The leading rotation region is oriented to extend radially further than the weight retaining region.

A robotic press assembly configured to apply force to a wheel, may include a selectively moveable arm that is operatively connected to a body portion at a first end thereof; and a press tool operatively connected to a second end of the moveable arm; wherein the press tool includes at least one mounting bracket maintaining a press tool thereon, the mounting bracket arranged on a platform, and a base operatively connected to the second end of the arm, the platform being slidably fixed to the base in order to adjust the lateral displacement of the press tool, and wherein the press tool is configured to apply force at the wheel.

A fixture for sticking balance blocks to the surface of a hub includes a base, in which a fixed plate is welded to one side of the upper end of the base, a slide rail butted to the fixed plate is connected to the other side of the base by bolts, a sliding block is connected to the slide rail in a sliding manner, the middle positions of the fixed plate and the sliding block are respectively connected with a first roller and a second roller of the same type by bearings, each of the first roller and the second roller is sleeved with a rubber sleeve of the same specification, and a support table is mounted under the base.

A method for tuning a vibration response of an aircraft system is disclosed, where the aircraft system comprises an airframe and at least one engine dynamically coupled, the at least one engine having an engine rotor including a nose cone. The method comprises obtaining a range of frequencies associated with at least one resonance mode of the aircraft system and adding mass within the nose cone to offset at least one dominant excitation frequency of the turbofan engine outside the range of frequencies associated with the at least one resonance mode of the aircraft system. A method of tuning dynamic coupling of an aircraft system comprising an airframe and an engine mounted thereto is also disclosed.

A method for tuning a vibration response of an aircraft system is disclosed, where the aircraft system comprises an airframe and at least one engine dynamically coupled, the at least one engine having an engine rotor including a nose cone. The method comprises obtaining a range of frequencies associated with at least one resonance mode of the aircraft system and adding mass within the nose cone to offset at least one dominant excitation frequency of the turbofan engine outside the range of frequencies associated with the at least one resonance mode of the aircraft system. A method of tuning dynamic coupling of an aircraft system comprising an airframe and an engine mounted thereto is also disclosed.

A balancing weight is disclosed. The balancing weight is engageable in a hole defined in a rotor, the hole having a predetermined cross-sectional dimension. The balancing weight comprises: a head having a predetermined weight, and a shank extending axially from the head. The shank includes at least two portions expandable in a direction transverse to a hole engagement direction between a first position in which a cross-sectional dimension of the shank is less than the predetermined cross-sectional dimension of the hole and a second position in which the cross-sectional dimension of the shank is greater than the predetermined cross-sectional dimension of the hole in the rotor. A method for installing a balancing weight to an engine rotor is also disclosed.

A balancing weight is disclosed. The balancing weight is engageable in a hole defined in a rotor, the hole having a predetermined cross-sectional dimension. The balancing weight comprises: a head having a predetermined weight, and a shank extending axially from the head. The shank includes at least two portions expandable in a direction transverse to a hole engagement direction between a first position in which a cross-sectional dimension of the shank is less than the predetermined cross-sectional dimension of the hole and a second position in which the cross-sectional dimension of the shank is greater than the predetermined cross-sectional dimension of the hole in the rotor. A method for installing a balancing weight to an engine rotor is also disclosed.