Described is an adjustable guide vane ring of a turbomachine having an axially split inner ring, on which a brush seal is configured, an inner ring for a guide vane ring of this kind, as well as a turbomachine.

Aspects of the disclosure are directed to a brush seal comprising: a bristle pack that includes: a first plurality of bristles, each of the first plurality of bristles having a first dimension, and a second plurality of bristles, each of the second plurality of bristles having a second dimension that is different from the first dimension, where a ratio of the first dimension to the second dimension has a range of 2:1 to 5:1.

A method treats a brush seal at a tip end of the brush seal. The method includes contacting the tip end of the brush seal to an oxidation-resistant, wear-resistant coating composition and heat-treating a distal portion of the bristles to form an oxidation-resistant, wear-resistant coating on the distal portion from the oxidation-resistant, wear-resistant coating composition. A brush seal includes a brush support and bristles extending from the brush support with a distal portion coated by an aluminide diffusion coating. A brush seal assembly includes a non-rotary component and a rotary component. The non-rotary component includes a brush seal including a bristle pack. The bristle pack includes bristles extending from a brush support with a distal portion coated by an aluminide diffusion coating. The rotary component has a sealing surface contacting the distal portion of the brush seal to form a turbine seal between the rotary component and the non-rotary component.

An interface assembly for a combustor includes an interface housing having a channel defined by a forward wall and at least one aft wall segment, the aft wall segment operatively coupled to an aft flange of a flow sleeve. Also included is a piston ring fittingly disposed in the channel.

The invention is characterized by a rotary external housing and the attachment of the movable blades to the inner side of said housing, and by the attachment of the fixed (or static) blades to a shaft or other static central element, irrespective of whether compression or expansion occurs in one or more stages. The proposed attachment eliminates the radial gap in the region that transfers maximum energy to the fluid, thereby drastically reducing the problems due to stalling at the boundary layer. In this way, there is no drop in the mechanical performance of small axial turbines and compressors with a less favorable ratio of radial gap to housing diameter, an aspect that has prevented more generalized use thereof. The fixed blades, by not transferring energy to the fluid and decelerating the rotation thereof, encounter fewer stalling problems than movable blades.

A seal assembly in a gas turbine engine is presented. The seal assembly is arranged at a forward side of an inner compressor exit diffusor. The seal assembly is arranged between an outlet guide vane assembly and the forward side of the inner compressor exit diffusor to reduce cooling air leakage therebetween or is arranged between adjacent outlet guide vane assemblies to reduce cooling air leakage therebetween. The seal assembly includes a plurality of seal segments. The seal assembly includes at least one seal, such as a brush seal.

Disclosed is a static seal arrangement for sealing a gap between a first static component and a second static component of a turbomachine such as an aircraft engine or a static gas turbine, having a brush seal held distant from a hot gas, this brush seal being arranged standing or vertical with its clamping section that can be surrounded by cooling air in a radially outer clamping space relative to the gap, and forming a radial sealing site with the first component and an axial sealing site with the second component; also disclosed is a turbomachine.

A seal assembly for a turbomachine. The turbomachine includes a rotating shaft extending along a centerline and a fixed housing positioned exterior to the rotating shaft in a radial direction relative to the centerline. The seal assembly includes a sump housing at least partially defining a bearing compartment for holding a cooling lubricant. The seal assembly further includes a bearing supporting the rotating shaft. In addition, the seal assembly also includes a sump seal at least partially defining the bearing compartment. A pressurized housing of the seal assembly is positioned exterior to the sump housing and defines a pressurized compartment to at least partially enclose the sump housing. Further, a non-contacting carbon seal is positioned between the rotating shaft and the fixed housing to at least partially define the pressurized compartment to enclose the sump housing.

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 gas turbine engine includes a turbine section having a turbine rotor and at least one blade extending outwardly of the turbine rotor. The turbine rotor rotates about an axis of rotation. A blade outer air seal is positioned radially outward of the at least one blade. The blade outer air seal has an axially forward hook and an axially aft hook supported to static structure. An axial seal is attached to static structure forward of the forward hook, and has a sealing portion extending in an aft direction. A sealing surface member is positioned intermediate an aft end of the axial seal and a forward end of the forward hook to provide a sealing surface for sealing between the seal and the blade outer air seal.