A nose cone assembly is provided comprising a nose cone, a support ring on which the nose cone is mounted, and an insulating layer disposed between the nose cone and the support ring, the insulating layer at least partially comprising glass fibres. A composite nose cone is also provided comprising an attachment region A, in which composite fibres are oriented substantially perpendicular to an axis of rotation of the nose cone, and an impact region I, in which composite fibres are oriented substantially parallel to the axis of rotation of the nose cone. Also provided is a support ring for a nose cone assembly, the support ring comprising an annular main body and an annular projecting attachment flange, the attachment flange terminating in a plurality of circumferentially spaced attachment tabs, wherein the attachment flange forms with the main body a cross section having at least two C curves.

A gas turbine engine includes a circumferential row of blades, with the blades having respective blade tips. A seal is disposed about the blades. The seal has an abradable layer which the tips of the blades, at times, rub against when the blades rotate. The rubbing produces a maximum temperature at the abradable layer. The abradable layer includes a metal matrix and microballoons dispersed in the metal matrix. The microballoons are formed of a glass that has a glass transition temperature that is approximately 50 F. to 300 F. greater than the maximum temperature.

Example techniques may include depositing a slurry on at least a predetermined surface region of a ceramic matrix composite substrate. The slurry may include a solvent and particles comprising at least one of silicon metal or silicon carbide. The slurry may be dried to form a wicking layer on the predetermined surface region. The ceramic matrix composite substrate and the wicking layer may be heated to a temperature of at least 900 C. to wick at least one wickable species from the ceramic matrix composite substrate into the wicking layer. Substantially all of the wicking layer may be removed from the predetermined surface region. Example articles may include a ceramic matrix composite substrate. A wicking layer may be disposed on at least a predetermined surface region of the ceramic matrix composite substrate. The wicking layer may include at least one wicked species wicked from the ceramic matrix composite substrate.

A fragmenting nozzle system includes a first nozzle at least partially disposed within a second nozzle. The first nozzle includes an ablative shell, a syntactic foam support disposed between the ablative shell and the second nozzle, and an ignition system disposed at least partially within the syntactic foam support. For example, the ignition system is operable to generate a controlled-energy deflagration pressure wave that fragments the first nozzle but not the second nozzle.

An environmental barrier coating, comprising a substrate containing silicon; an environmental barrier layer applied to the substrate; the environmental barrier layer comprising an oxide matrix; an oxidant getter phase interspersed throughout the oxide matrix; and a self-healing phase interspersed throughout the oxide matrix.

A gas turbine engine includes a circumferential row of blades, with the blades having respective blade tips. A seal is disposed about the blades. The seal has an abradable layer which the tips of the blades, at times, rub against when the blades rotate. The rubbing produces a maximum temperature at the abradable layer. The abradable layer includes a metal matrix and microballoons dispersed in the metal matrix. The microballoons are formed of a glass that has a glass transition temperature that is approximately 50 F. to 300 F. greater than the maximum temperature.

An apparatus a multiple layer structure having a sub-portion defining an impact zone, and having an inner composite fiber layer, an outer composite fiber layer overlying the inner composite fiber layer, and a woven glass layer, where the inner composite fiber layer, outer composite fiber layer, and the woven glass layer overly the impact zone.

In some examples, method including forming an EBC layer on a substrate, wherein the EBC layer exhibits an initial porosity; forming a layer of silicate glass on a surface of the EBC layer; and melting the silicate glass on the surface of the EBC layer to infiltrate the EBC layer with the molten silicate glass to decrease the porosity of the EBC layer from the initial porosity to a final porosity.

A fibrous texture has the shape of a strip extending in a longitudinal direction over a determined length between a proximal portion and a distal portion and in a lateral direction over a determined width between a first lateral edge and a second lateral edge. The fibrous texture has a three-dimensional or multi-layer weaving between a plurality of layers of warp strands extending in the longitudinal direction and a plurality of layers of weft strands extending in the lateral direction, the fibrous texture including first and second longitudinal sections extending over a width from the first or second lateral edge smaller than the determined width of the fibrous texture along the lateral direction. The first and second longitudinal sections each include warp strands and weft strands constituted by carbon fibers. The fibrous texture further includes a third section present between the first and second sections.

A method for forming a composite part of a gas turbine engine. The method includes assembling the composite part of a first composite material and a second composite material. The second composite material defines an outer surface of the composite part, and is selected to be curable at a cure temperature generated by heat from operation of the engine. The first composite material is selected to have an operating temperature limit less than the cure temperature. The method includes placing the composite part within the engine so that, in use, the second composite material is cured by exposure to the heat generated from operation of the engine. The second composite material thermally shields the first composite material from the heat generated from operation of the engine. The method includes operating the engine to cure the second composite material.