Provided are a sliding member for sealing and a seal device that exhibit good sealing performance even when used in an environment where silicon oxide is likely to be deposited.

A sliding member for sealing includes a sintered body consisting of 1.0 to 12.5 wt % of cerium oxide, a combination of 20 to 50 wt % of graphite and graphitizable carbon, and a remainder of non-graphitizable carbon. The sliding member for sealing is used as, for example, a rotary seal ring or a stationary seal ring.

An electrical submersible pumping system includes thrust bearings and radial bearings fabricated from a micro-grained polycrystalline diamond compact (“USPDC”) material that is ultra-strong; and where the USPDC is produced using a catalyst free process. In examples, all components of the bearings are formed from the ultra-strong USPDC material. Pads are in the bearings that have a contact surface, and the pads selectively tilt about a tilt member in response to variations in an opposing contact surface. The tilt members are attached to or otherwise associated with the pads, and are in contact with a resilient member that improves tilting response of the pads. The resilient members are encased in jackets that cover surfaces of the resilient members not in contact with the tilt members. The jackets are set in channels formed in structure of the bearings.

The disclosure describes composite liners (such as acoustic panels, fan track liners, and/or ice impact panels or boxes for turbofan engines) and techniques for forming composite liners. In some examples, the composite liner includes at least one region comprising a reinforcement architecture comprising a matrix material, a plurality of relatively tough polymer-based reinforcement elements, and a plurality of second reinforcement elements. The plurality of relatively tough polymer-based reinforcement elements and the plurality of second reinforcement elements are embedded in the matrix material.

A method for preparing a seal assembly for a gas turbine engine, comprising a seal comprising a carbon material; and a seal seat positioned for rotation relative to the seal, wherein the method comprises the steps of: pre-filming a sealing surface of the seal seat with a carbon-based tribofilm; and assembling the seal seat relative to the seal in a gas turbine engine.

A seal land includes a seal land body that extends circumferentially about an axis and radially between an inner seal land side and an outer seal land side. The seal land body is configured with a plurality of fluid passages arranged about the axis. A first of the fluid passages includes an inner passage segment and an outer passage segment fluidly coupled with the inner passage segment. The inner passage segment extends along a first trajectory within the seal land body towards the outer passage segment. The outer passage segment extends along a second trajectory within the seal land body away from the inner passage segment and towards the outer seal land side. The second trajectory is different than the first trajectory and includes a radial component and a circumferential component.

A seal housing may comprise an aft flange, an outer diameter (OD) ring and a stopper. The stopper may extend radially inward from a radially inner surface of OD ring. The stopper may be configured to interface with a monobloc carbon seal. The stopper may comprise a circumferential stopping portion and an axial stopping portion. There may be a plurality of the stopper.

A fluid delivery device is provided that includes a sleeve and a tube. The sleeve extends axially along an axis between a sleeve first end and a sleeve second end. The sleeve extends radially from a sleeve inner side to a sleeve outer side. The sleeve extends circumferentially around the axis thereby forming an internal bore at least partially formed by a bore surface at the sleeve inner side. The internal bore extends axially along the axis through sleeve between the sleeve first end and the sleeve second end. The tube is connected to the sleeve and projects out from the sleeve outer side to a tube distal end. The tube is configured with a delivery device fluid passage fluidly coupled with the internal bore. The delivery device fluid passage extends radially through the tube to a fluid passage outlet at the tube distal end.

Composite components and methods for forming composite components are provided. For example, a composite component of a gas turbine engine comprises a composite material, a plurality of piezoelectric fibers, and an anti-icing mechanism. The anti-icing mechanism is in operative communication with the piezoelectric fibers such that the anti-icing mechanism is activated by one or more electrical signals from the piezoelectric fibers. In exemplary embodiments, the composite component is a composite airfoil and the anti-icing mechanism is one or more heating elements. Methods for forming composite components may comprise forming piezoelectric plies comprising piezoelectric fibers embedded in a matrix material; forming reinforcing plies comprising reinforcing fibers embedded in the matrix material; laying up the piezoelectric and reinforcing plies to form a ply layup; and processing the ply layup to form the composite component. Methods including forming a piece of piezoelectric material that is adhered to a composite component also are provided.

A method comprises discharging from a metal vaporization device a vapor of a metal or a metal precursor to a chemical vapor infiltration device where the chemical vapor infiltration device is in fluid communication with the metal vaporization device. The chemical vapor infiltration device contains a preform containing ceramic fibers. The preform is infiltrated with a metallic coating or a coating of a metallic precursor along with a ceramic precursor coating. The metallic coating and/or the metallic precursor coating and the ceramic precursor coating are applied sequentially or simultaneously.

A shaft failure protection system includes an engine core comprising a turbine, a compressor, and a shaft connecting the turbine and compressor; a first braking element connected to a rotating part of the turbine; and a second braking element connected to a static part of the turbine. The first and second braking elements are arranged at an axial distance under normal operating conditions and configured to contact each other in case of a failure of the shaft and an associated axial displacement of the rotating part. The first braking element includes a first friction material and the second braking element comprises a second friction material, wherein the first and second friction materials each comprise a carbon-silica composite or a carbon-fibre-reinforced carbon. Upon shaft failure and associated axial displacement of the rotating part, the first and second friction materials contact each other to reduce speed of the rotating part.