A rotary machine includes a rotary shaft that rotates around an axis, a plurality of rotor blades arranged on an outer peripheral side of the rotary shaft in a circumferential direction in which the rotor blade has a blade root, a platform, and a blade main body; and each damper member provided radially inward of the platform, in which the platform includes a first end surface that faces one side in the circumferential direction, and a second end surface that faces the other side in the circumferential direction so that the second end surface faces the first end surface of the adjacent other platform, and the damper member includes a first damper provided on the first end surface and having a first abutting surface, a second damper that has a second abutting surface slidably abutting the first abutting surface of the first damper and is abuttable on the second end surface, and an elastic member that bonds together the first damper and the second damper.

A stator assembly for a gas turbine engine includes an arcuate shroud including a shroud pocket, the shroud pocket having a shroud slot extending therethrough. A stator vane is insertable into the shroud pocket and includes a vane slot extending therethrough. A strap extends through the shroud slot and the vane slot to retain the vane to the shroud. A gas turbine engine includes a combustor and a stator and case assembly in in fluid communication with the combustor. The stator and case assembly includes a case defining a working fluid flowpath for the gas turbine engine and a stator assembly secured at the case.

A stator assembly for a stator of a gas turbine engine is provided. The stator assembly having: a shroud defining a cavity; a plurality of inserts located within the cavity, each of the plurality of inserts defining a cavity; a plurality of vanes secured to the shroud, wherein each of the plurality of vanes has a tab portion located in the cavity of the shroud; and a rubber material disposed in the cavity of the shroud, the rubber material securing the tab portion of each of the plurality of vanes to the shroud.

A rotor in BLISK or BLING design of an aircraft engine, comprising: a rotor disc that, at its radially outer area, forms an annulus which delimits the flow channel of the aircraft engine radially inside; and a plurality of rotor blades that project from the annulus; wherein the rotor disc forms a first structure and a second structure which are arranged at a distance from each other in the radial direction, wherein the first structure and the second structure respectively have an arm that protrudes upstream and/or downstream in the axial direction. An arm of the first structure arranged upstream and an arm of the second structure arranged upstream and/or an arm of the first structure arranged downstream and an arm of the second structure arranged downstream are connected to each other by means of a damping element that comprises an elastomer or is formed from an elastomer.

An inlet cone for an aircraft turbomachine, having at least one first portion made of a first material, referred to as rigid material, and at least one second portion made of a second material which has a hardness less than that of said first material and which is referred to as flexible material, these second portions being configured to deform elastically in the radial direction with respect to the axis when the cone is being driven to rotate.

Provided is a vibration reduction device for stator vanes (30) positioned behind rotor blades (28) in a turbo machine, comprising an annular base member (80) having a cylindrical shape concentric around a central axis of the casing and supporting base ends of the stator vanes which extend radially inward from an inner circumferential surface of the base member, an elastomeric damping member (100) surrounding and in slidable contact with an outer circumferential surface of the base member, and a preloading member (102) surrounding an outer circumferential surface of the elastomeric damping member and configured to apply a preload directed radially inward to the elastomeric damping member.

A bearing for a turbomachine variable pitch stator vane pivot mounted in a bore of a casing of the turbomachine and including a bushing integral with the bore and allowing rotation of a pivot rod within the casing, and additionally a ring mounted so as to be integral with the pivot rod inside the bushing and including an outer part providing the stiffening of the ring and an inner part integral with the outer part and providing a damping function.

A gas turbine engine includes an annular structure disposed around an engine central longitudinal axis of the gas turbine engine. The annular structure defines an annular channel and comprises a first density, according to various embodiments. The gas turbine engine may further include a weight-saving filler disposed within the annular channel. The weight-saving filler may have a second density that is less than the first density. The gas turbine engine may further include an annular retention strap disposed around the engine central longitudinal axis of the gas turbine engine. The annular retention strap is at least partially embedded in the weight-saving filler, according to various embodiments.

The disclosure describes composite nosecones and techniques for forming composite nosecones including a matrix material, relatively higher-modulus reinforcement elements, and relatively tougher polymer-based reinforcement elements. An example composite nosecone includes a body substantially symmetrical around a central axis. The body includes a side wall defining a diameter of the body that increases from a forward side of the body to an aft side of the body. The body includes a composite material including a plurality of relatively higher-modulus reinforcement elements, a plurality of relatively tougher polymer-based reinforcement elements, and a matrix material substantially encapsulating the plurality of relatively higher-modulus reinforcement elements and the plurality of relatively tougher polymer-based reinforcement elements. The plurality of relatively higher-modulus reinforcement elements are different from the plurality of relatively tougher polymer-based reinforcement elements.

A fan of a gas turbine engine includes a plurality of fan blades secured to a rotor, each of the plurality of fan blades having an airfoil secured to the rotor at one end, wherein the airfoil comprises pockets filled with an elastomeric composite.