A method for producing a rotating turbine blade and tuning the natural frequencies of the blade is disclosed that changes the second effective beam length of the blade thereby changing the separation between the first natural frequency and the second natural frequency of the blade.

A method for producing a rotating turbine blade and tuning the natural frequencies of the blade is disclosed that changes the second effective beam length of the blade thereby changing the separation between the first natural frequency and the second natural frequency of the blade.

A coating is applied to a base material. The coating comprises a viscoelastic layer having a surface in which cavities are formed; and a constraint layer. The viscoelastic layer is disposed on the base material, and the constraint layer is disposed on, and partially bonded, at an interface, to the viscoelastic layer over the surface in which the cavities are formed. The cavities are filled with particles configured for vibration and frictional interaction at the partially bonded interface between the partially bonded viscoelastic layer and the constraint layer. A turbine blade having an airfoil with the subject coating is also provided.

A coating is applied to a base material. The coating comprises a viscoelastic layer having a surface in which cavities are formed; and a constraint layer. The viscoelastic layer is disposed on the base material, and the constraint layer is disposed on, and partially bonded, at an interface, to the viscoelastic layer over the surface in which the cavities are formed. The cavities are filled with particles configured for vibration and frictional interaction at the partially bonded interface between the partially bonded viscoelastic layer and the constraint layer. A turbine blade having an airfoil with the subject coating is also provided.

An adjustable blade root spring device for turbine blade fixation in turbomachinery. The device is designed to be placed in a space in a rotor disk cavity adjacent to a tip of a blade root fir tree, where the device applies a radial outward force on the turbine blade to fix the blade position in the rotor disk. The device includes an accordion-shaped spring which is compressed by a bolt and a coil spring. When the accordion spring is compressed in length, it increases in height and makes contact with the rotor disk and the turbine blade. The force of the accordion spring on the turbine blade can be adjusted via the bolt, and the coil spring provides an increased compliance range. The device can be inserted into the space without scraping against the blade root or the rotor disk, and expanded once it is in position.

An adjustable blade root spring device for turbine blade fixation in turbomachinery. The device is designed to be placed in a space in a rotor disk cavity adjacent to a tip of a blade root fir tree, where the device applies a radial outward force on the turbine blade to fix the blade position in the rotor disk. The device includes an accordion-shaped spring which is compressed by a bolt and a coil spring. When the accordion spring is compressed in length, it increases in height and makes contact with the rotor disk and the turbine blade. The force of the accordion spring on the turbine blade can be adjusted via the bolt, and the coil spring provides an increased compliance range. The device can be inserted into the space without scraping against the blade root or the rotor disk, and expanded once it is in position.

A bladed rotor system for a turbomachine includes a circumferential row of blades mounted on a rotor disc, and includes a plurality of under-platform dampers. Each damper is located between adjacent blade platforms. The plurality of dampers includes a first set of dampers and a second set of dampers. The dampers of the first set are distinguished from the dampers of the second set by a cross-sectional material distribution in the damper that is unique to the respective set. Dampers of the first set and the second set are positioned alternately in a periodic fashion in a circumferential direction, to provide a frequency mistuning to stabilize flutter of the blades.

A turbine damper may be provided that may include an elongated body sized to fit inside a turbine blade, the elongated body elongated along a radial direction of the turbine blade relative to a rotation axis of the turbine blade, and plural dampening masses coupled with the elongated body and disposed at different locations along the radial direction. The plural dampening masses may be one or more of sized to dampen different vibration modes of the turbine blade, or moveable relative to and along the elongated body in the radial direction.

A turbine damper may be provided that may include an elongated body sized to fit inside a turbine blade, the elongated body elongated along a radial direction of the turbine blade relative to a rotation axis of the turbine blade, and plural dampening masses coupled with the elongated body and disposed at different locations along the radial direction. The plural dampening masses may be one or more of sized to dampen different vibration modes of the turbine blade, or moveable relative to and along the elongated body in the radial direction.

The invention relates to a method for producing a mistuning component. The method comprises the following steps: a) producing a container (34) having at least one chamber (36); b) producing a lid (32, 32′); c) inserting at least one impulse element into the chamber (36); d) joining the lid (32, 32′) and the container (36), wherein joining is carried out by soldering/brazing.