A turbine blade includes: a platform; an airfoil portion extending from the platform in a blade height direction and having a pressure surface and a suction surface extending between a leading edge and a trailing edge; a blade root portion positioned opposite to the airfoil portion across the platform in the blade height direction and having a bearing surface; and a shank positioned between the platform and the blade root portion. The shank has a cross-section which is perpendicular to the blade height direction of the airfoil portion, and in which a line segment connecting a widthwise center position of a leading-edge-side end portion of the shank and a widthwise center position of a trailing-edge-side end portion of the shank is sloped to a center line between a pressure-surface-side contour of the blade root portion and a suction-surface-side contour of the blade root portion.

A turbine blade includes: a platform; an airfoil portion extending from the platform in a blade height direction and having a pressure surface and a suction surface extending between a leading edge and a trailing edge; a blade root portion positioned opposite to the airfoil portion across the platform in the blade height direction and having a bearing surface; and a shank positioned between the platform and the blade root portion. The shank has a cross-section which is perpendicular to the blade height direction of the airfoil portion, and in which a line segment connecting a widthwise center position of a leading-edge-side end portion of the shank and a widthwise center position of a trailing-edge-side end portion of the shank is sloped to a center line between a pressure-surface-side contour of the blade root portion and a suction-surface-side contour of the blade root portion.

The leading edge, the trailing edge, or both may be axially offset for a portion of the airfoils in a disk. By offsetting the airfoils, the downstream wake energy to the next stage of airfoils may be decreased. By staggering airfoils which are offset with airfoils that are not offset, the wake shapes from the airfoils may be out of phase and will not excite the downstream airfoils as much as conventional systems. This may decrease vibration and associated vibratory stresses in the system.

A stator assembly for a gas turbine engine includes an arcuate outer shroud, an arcuate inner shroud radially spaced from the outer shroud and a plurality of stator vanes extending from the outer shroud to the inner shroud. A volume of potting is located at the inner shroud and at the outer shroud to retain the plurality of stator vanes thereat. A stator and case assembly includes a case defining a working fluid flowpath and a stator assembly positioned at the case. The stator assembly includes a plurality of stator segments arranged circumferentially about an engine axis, each stator segment including an arcuate outer shroud secured to the case, an arcuate inner shroud, and a plurality of stator vanes extending from the outer to inner shroud. A volume of potting is located at the inner shroud and at the outer shroud to retain the plurality of stator vanes thereat.

A stator assembly for a gas turbine engine includes an annular outer shroud, an annular inner shroud radially spaced from the outer shroud and a plurality of stator vanes extending from the outer shroud to the inner shroud. A volume of potting is located at the inner shroud and at the outer shroud to retain the plurality of stator vanes thereat. A stator and case assembly for a gas turbine engine includes a case defining a working fluid flowpath for the gas turbine engine and a stator assembly located at the case. The stator assembly includes an annular outer shroud secured to the case, an annular inner shroud secured to the case and a plurality of stator vanes extending from the outer to the inner shroud. A volume of potting is located at the inner shroud and at the outer shroud to retain the plurality of stator vanes thereat.

The invention relates to a modular nozzle ring for a turbine stage of a continuous flow machine. The modular nozzle ring has a carrier system having an an adjustment ring, and a blade module having a blade leaf. The blade module is detachably connected to the carrier system. Furthermore, an adjustment angle of the blade leaf by the carrier system, in particular by the adjustment ring spaced apart from a flow channel, is specified, which adjustment angle is unchangeable during operation. The blade module is designed to be detachably pressed to a turbine housing part on the flow side, in particular by the adjustment ring. The invention furthermore relates to a blade module for a modular nozzle ring of a turbine stage and the use of a carrier system for a modular nozzle ring.

A turbomachine blade system, in particular for a compressor or turbine stage of a gas turbine, which includes at least one blade, in particular a moving or guide blade, and at least one moving body for reducing the vibrations of this blade, at least one area of a guide for guiding the body and/or at least one area of a supporting structure for resiliently mounting the body and/or at least one area of the body being or becoming generatively manufactured together with at least one area of the blade, in particular of a vane and/or blade root and/or a shroud situated thereon.

A turbomachine blade system, in particular for a compressor or turbine stage of a gas turbine, which includes at least one blade, in particular a moving or guide blade, and at least one moving body for reducing the vibrations of this blade, at least one area of a guide for guiding the body and/or at least one area of a supporting structure for resiliently mounting the body and/or at least one area of the body being or becoming generatively manufactured together with at least one area of the blade, in particular of a vane and/or blade root and/or a shroud situated thereon.

A rotor blade system includes a rotor, a casing radially spaced apart from the rotor, and a plurality of blades coupled to the rotor and positioned between the rotor and the casing. The one or more of the plurality of blades have a radial length different from a remaining one or more of the plurality of blades so as to vary a tip gap between a tip of the one or more of the plurality of blades and the casing to break up a frequency content of a leakage vortex at the tip to modify natural frequencies of the plurality of blades and mode shapes to reduce or substantially eliminate flutter.

A vibration damping device according to an embodiment is a vibration damping device for a blade of a rotating machine, which includes at least one housing configured to be containable in a cavity formed under a platform of the blade, and to be detachable from the blade, and an attenuation material disposed in a vibration damping space formed inside the housing.