Sealing arrangements and rotor assemblies are provided. A sealing arrangement includes a stationary component, a rotating component spaced apart from the stationary component. A clearance is defined between the stationary component and the rotating component. The sealing arrangement further includes a plurality of magnets embedded within the rotating component. The sealing arrangement further includes a brush seal having a frame and a plurality of magnetically responsive filaments. The plurality of magnetically responsive filaments each extending from the frame to a free end. The plurality of magnetically responsive filaments are attracted to the rotating component by the plurality of magnets. The plurality of magnetically responsive filaments at least partially covering the clearance, such that a flow of fluid across the clearance is restricted.

A rotor for an axial turbomachine includes a drum formed of several parts including: composite rings made of composite material and metallic rings interposed between the composite rings. The metallic rings carry the rotor blades. The metallic rings have an axial branch axially overlapping the composite rings and at least one radial branch in contact with the composite rings.

A gas turbine engine includes, among other things, a bearing compartment, a shaft configured to rotate during operation of the gas turbine engine, and a sleeve configured to rotate with the shaft during operation of the gas turbine engine. The sleeve includes a variable radial dimension about a circumference of the sleeve. The engine further includes a seal statically mounted relative to the sleeve and configured to cooperate with the sleeve to seal the bearing compartment.

A seal for a rotor is provided. The rotor defines an axial direction, a circumferential direction, and a radial direction. The seal includes a first flexible element coupled to the rotor. The first flexible element extends in a first direction that is within forty five degrees of the axial direction.

A centrifugal compressor for HVAC application includes a rotary component rotatable about an axis, a static component, and a brush seal fixed to one of the static component and the rotary component. The brush seal includes bristles that contact the other of the static component and the rotary component.

A turbomachinery component of a gas turbine engine is disclosed having a number of techniques of reducing the effects of a gap flow between an airfoil member of the gas turbine engine and a wall of the gas turbine engine. The airfoil member can be variable and in one form is a variable turbine vane. In one embodiment a brush seal is included between the vane and the wall. In another form a wear surface is disposed between the vane and the wall. In yet another form a moveable member capable of being actuated to change position can be disposed between the vane and the wall to alter the size of a gap between the two.

A brush seal for a rotating machine, intended to be disposed between a first part and a second part of the rotating machine, the first and second parts being movable relative to each other about an axis, extending along an axial direction, the brush seal comprising a body intended to be attached to the first part, and a brush attached to the body, intended to be in contact with the second part, wherein the brush comprises at least a first group of bristles and a second group of bristles, at least one parameter of the bristles of the first group of bristles being different from the corresponding parameter of the bristles of the second group of bristles.

A shroud assembly for a gas turbine engine includes a plurality of shroud segments that are attached to a shroud support with an inter-segment joint defined between shroud segments. The shroud assembly also includes a cooling flow path cooperatively defined by the shroud support and the first shroud segment. The cooling flow path includes an internal cooling passage within the shroud segments. The cooling flow path includes an outlet chamber configured to receive flow from the internal cooling passage. The shroud assembly additionally includes a seal arrangement that extends across the inter-segment joint. The seal arrangement, the first shroud segment, and the second shroud segment cooperatively define a seal chamber that is enclosed.

A first-stage turbine vane supporting structure reduces chordal leakage between a first-stage turbine vane segment and its supporting ring. The structure includes a first-stage turbine vane segment including an outer platform, an inner platform, and a first-stage turbine vane disposed between the inner and outer platforms; an inner rail protruding from the inner platform in a longitudinal direction of the first-stage turbine vane; a supporting ring for supporting the first-stage turbine vane segment by engaging with the inner rail while facing one surface of the inner rail; a supporting member engaging with the supporting ring to define a U-shaped space bordered by three side surfaces surrounding the inner rail; and a flexible member interposed between the inner rail and one of the three side surfaces of the U-shaped space. A protrusion formed on the inner rail engages with a sealing surface of the supporting ring in an airtight manner.

A brush seal for sealing a leakage gap in an axial flow path between a relatively higher fluid pressure region and a relatively lower fluid pressure region, that includes an outer housing and an inner housing located at least partially within and configured for radial displacement relative to the outer housing, wherein the upstream facing inner surface of the outer housing is free of any protrusion toward the first downstream facing outer contact surface and second downstream facing outer contact surface.