An integrally bladed rotor for a turbomachine, in particular a compressor or turbine stage of a gas turbine, to which at least one separately formed impulse element housing (40; 40′) is fastened by at least one fastening element (30; 30′) which engages for this purpose into an opening (41) of the impulse element housing and into an opening (11) of the rotor, the impulse element housing having at least one cavity (44) in which at least one impulse element (5) is accommodated with play.

An integrally bladed rotor for a turbomachine, in particular a compressor or turbine stage of a gas turbine, to which at least one separately formed impulse element housing (40; 40′) is fastened by at least one fastening element (30; 30′) which engages for this purpose into an opening (41) of the impulse element housing and into an opening (11) of the rotor, the impulse element housing having at least one cavity (44) in which at least one impulse element (5) is accommodated with play.

A vibration mitigation coating for an integrally bladed rotor including a disk including an interior radius proximate an axis and an exterior radius distal from the axis, the disk including a substrate with an external surface, said external surface extends from the interior radius to the exterior radius; and a damping material disposed directly onto the external surface of the substrate.

A vibration mitigation coating for an integrally bladed rotor including a disk including an interior radius proximate an axis and an exterior radius distal from the axis, the disk including a substrate with an external surface, said external surface extends from the interior radius to the exterior radius; and a damping material disposed directly onto the external surface of the substrate.

High cycle fatigue (HCF) in a turbine wheel of a sector-divided dual volute turbocharger, particularly a turbocharger where the tongue-to-blade gap is as small as from 1-3% of the wheel diameter, is reduced, and energy extraction is optimized, using a turbine wheel with (blade stiffness/backwall stiffness×100) between 41 and 44.

An airfoil assembly for a turbine engine defines an axial direction, a radial direction, and a circumferential direction, and includes a first airfoil defining a first end along the radial direction, a first hub disposed on the first end of the first airfoil and having a first extension member extending at least partially in the radial direction, and a second airfoil adjacent to the first airfoil, the second airfoil defining a first end along the radial direction, a second hub disposed on the first end of the second airfoil and comprising a second extension member extending at least partially in the radial direction, and a circumferential bias assembly operable with the first extension member, the second extension member, or both for exerting a circumferential force on the first extension member, the second extension member, or both.

An airfoil assembly for a turbine engine defines an axial direction, a radial direction, and a circumferential direction, and includes a first airfoil defining a first end along the radial direction, a first hub disposed on the first end of the first airfoil and having a first extension member extending at least partially in the radial direction, and a second airfoil adjacent to the first airfoil, the second airfoil defining a first end along the radial direction, a second hub disposed on the first end of the second airfoil and comprising a second extension member extending at least partially in the radial direction, and a circumferential bias assembly operable with the first extension member, the second extension member, or both for exerting a circumferential force on the first extension member, the second extension member, or both.

The present disclosure is directed to an engine component for a gas turbine engine, the engine component including a substrate that includes a composite fiber and defines a surface. An energy harvesting fiber is positioned within the substrate.

A system includes an electric generator, a power electronics system, a first heat exchanger, and a second heat exchanger. The electric generator includes a turbine wheel, a rotor, and a stator. The turbine wheel is configured to receive process gas and rotate in response to expansion of the process gas flowing through the electric generator. The rotor is configured to rotate with the turbine wheel. The electric generator is configured to generate electrical power upon rotation of the rotor within the stator. The power electronics system is configured to receive the electrical power from the electric generator and convert the electrical power to specified power characteristics. A heat transfer fluid receives waste heat from the power electronics system through the first heat exchanger. The heat transfer fluid transfers the received waste heat to the process gas through the second heat exchanger.

A vibration mitigation coating for an integrally bladed rotor including a disk including an interior radius hub proximate to an axis and an exterior radius flange distal from the axis, blades originating from the exterior radius flange portion of the disk, the blades extend from the exterior radius flange at an exterior radius flange outer face; the disk including a substrate with an external surface, the external surface extends from the interior radius hub to the exterior radius flange and along the exterior radius flange outer face; and a damping material disposed directly onto the external surface of the substrate, the damping material is located radially between the interior radius hub and the exterior radius flange and along the exterior radius flange outer face and between the blades.