An blade outer air seal support assembly includes a main support member configured to support a blade outer air seal. The main support member extends generally axially between a leading edge portion and a trailing edge portion. The leading edge portion is configured to be slidably received within a groove established by the blade outer air seal. A support tab extends radially inward from the main support member toward the blade outer air seal. The support tab configured to contact an extension of the blade outer air seal to limit relative axial movement of the blade outer air seal. A gusset spans between the support tab and the main support member.

A seal carrier (63) for a turbomachine (60) which is assembled from seal carrier segments, is provided. The seal carrier segments each have a seal structure (1a, b) on the radially inward side. These seal structures (1a, b) are either interleaved in the circumferential direction (4) such that a cross-sectional plane containing the longitudinal axis (2) of the turbomachine (60) intersects both the first seal structure (1a) and the second seal structure (1b), or the seal structures (1a, b) rest against each another.

A component for a gas turbine engine includes an airfoil section including a free end and an abrasive coating sprayed onto the free end, the abrasive coating including a polymer matrix and an abrasive filler, the abrasive filler between about 50%-75% by volume of the abrasive coating.

An abradable sealing element is positioned radially outwardly of a plurality of aerofoil blades of a gas turbine engine. The abradable sealing element comprises a radially inwardly facing surface region and a plurality of cooling holes.

The radially inwardly facing surface region comprises a wall structure, with the wall structure having one or more radially inwardly projecting walls formed by additive layer, powder fed, laser weld deposition.

Each of the inwardly projecting walls is continuous and defines a plurality of repeating units arranged circumferentially around the radially inwardly facing surface region, each repeating unit is open at a radially inwardly facing side of the sealing element, and each repeating unit comprises a plurality of curved portions forming a multi-lobed profile shape. Each cooling hole is provided in the radially inwardly facing surface region at a position within the multi-lobed profile shape.

An abradable seal includes a seal element that is formed of a polymer matrix with thermally conductive microspheres dispersed through the polymer matrix. The polymer matrix has a polymer matrix thermal conductivity and the microspheres have a microsphere thermal conductivity that is greater than the polymer matrix thermal conductivity.

A method includes providing a ceramic matrix composite (CMC) seal arc segment that has radially inner and outer sides, attaching an abradable layer on the radially outer side of the CMC seal arc segment, providing a carrier to support the CMC seal arc segment, the carrier including a ridge, and sliding the CMC seal arc segment relative to the carrier such that during the sliding the ridge cuts a groove into the abradable layer, the ridge remaining disposed in the groove to thereby provide a labyrinth seal that partitions the cooling cavity between the carrier and the CMC seal arc segment into sub-cavities.

An air seal for use in a gas turbine engine. The seal includes a thermally sprayed abradable seal layer. The abradable material is composed of aluminum powder forming a metal matrix, and co-deposited methyl methacrylate particles and/or hexagonal boron nitride particles embedded as filler in the metal matrix.

The invention relates to a composition for an abradable seal of a turbomachine, the composition comprising an aluminum base, nickel powder, polyester powder. The invention also relates to an outer casing of a low-pressure compressor of an axial-flow turbomachine with an abradable seal surrounding an annular row of rotor blades. The seal comprises a rounded support covered with a layer of abradable material comprising a metallic phase mainly made of aluminum and with nickel in a lesser proportion. The abradable material additionally comprises from 25% to 55% of additive, such as polyester, methyl methacrylate, hexagonal boron nitride, calcium fluoride. The support is segmented, and forms an organic matrix composite outer casing of the compressor. The invention also proposes a process for producing an abradable seal by plasma spraying an AlNi-polyester powder.

A gas turbine engine component includes a passage and a geometrically segmented coating section adjacent the passage. The geometrically segmented coating section includes a wall that has a first side bordering the passage and a second side opposite the first side. The second side includes an array of cells, and there is a coating disposed over the array of cells. The coating defines an exterior side. A cooling passage extends through the wall and the coating. The cooling passage fluidly connects the passage and the exterior side.

A method for manufacturing a metallic component especially configured and designed for a turbomachine includes a) for a precision-casting process, a wax model with a wax structure is produced, subsequently b) the tip of the wax structure is thermally and/or mechanically treated such that a region with an undercut is formed on the wax structure, subsequently c) the metallic component is manufactured from the wax model in the precision-casting process, with a component structural element with an undercut forming on a surface of the component, and d) the component structural element is provided at least partially with a ceramic coating, a plastic-containing coating, in particular a fiber composite layer and/or a plastic component.