A tuned mass damper for reducing vibration on a component includes a shaft connector member configured to be coupled to the component and a cable termination member. The tuned mass damper also includes at least one cable coupled to the shaft connector member and to the cable termination member such that vibration of the component is transferred to the at least one cable via the shaft connector member and increased or decreased by the at least one cable.

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.

Discharge grate intended to be mounted inside or at the outlet of a conduit of a discharge valve of a turbine engine of an aircraft, the discharge grate comprising an upstream face intended to receive a gas flow, a downstream face parallel to the upstream face and intended to deliver the gas flow received on the upstream face, and orifices passing through the perforated plate from the upstream face to the downstream face and intended to convey the gas flow through the perforated plate. The discharge grate comprises for each orifice of the perforated plate a tubular channel, coaxial with the orifice with which it is associated, and projecting from the downstream face of the perforated plate.

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.

The present document relates to an assembly for retaining a gear train in a turbomachine, the assembly comprising an annular casing (44) in which is engaged an annular part (48) rotatably locked in the casing (44) by annular means of cogging comprising first annular means of coupling (50) formed on the annular part and co-operating with second annular means of coupling formed on the annular casing (44), wherein a film of oil is formed in an annular space bounded between the first means of coupling (50) and the second means of coupling.

The invention relates to a rotor for integration in a turbomachine, with a rotor base body, wherein, on the rotor base body in a rotor outer space of the rotor, at least one blade element or airfoil is mounted, wherein the rotor base body extends in an axial direction of the rotor and comprises a connecting section, which extends in an axial direction of the rotor for connection to at least one further rotor and separates the rotor outer space from a rotor inner space of the rotor, wherein the connecting section comprises, in the axial direction, at a front side, preferably in the axial direction at a downstream-lying front side, a balancing flange, wherein the balancing flange is configured for compensating an imbalance of the rotor and extends in the radial direction in the rotor outer space, at least in sections.

A blade for a turbo machine is provided. The blade for a turbo machine includes an airfoil body extending in a radial direction and including a suction side surface and a pressure side surface opposite to the suction side surface with respect to a circumferential direction extending across the radial direction, and a snubber structure including a first snubber element protruding in the circumferential direction from the suction side surface of the airfoil body and a second snubber element protruding in the circumferential direction from the pressure side surface of the airfoil body, wherein the first snubber element is connected to the suction side surface of the airfoil body by a concave curved first transition portion having a first radius, and the second snubber element is connected to the pressure side surface of the airfoil body by a concave curved second transition portion having a second radius, the first radius being smaller than the second radius.

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.

Curved beams stacked structures-compliant shrouds for gas turbine engines are disclosed. An example shroud assembly comprising a plurality of concave curved beams, a plurality of convex curved beams, and a plurality of bumpers, wherein a first concave curved beam of the plurality of concave curved beams is inversely coupled to a first convex curved beam of the plurality of convex curved beams, a second concave curved beam of the plurality of concave curved beams, inversely coupled to a second convex curved beam of the plurality of convex curved beams, the first and second concave curved beams configured to stack on top of the first and second convex curved beams, a first bumper of the plurality of bumpers coupled to the first and second concave curved beams, and a second bumper of the plurality of bumpers coupled to the first and second convex curved beams.