Apparatus and system for containing a rupture of a duct. The apparatus includes an air-permeable sheet, such as a wide-weave fiberglass sheet. The air-permeable sheet includes a strap arranged on a first side of the sheet such that it forms diamond-shaped patterns along a longitudinal axis. The strap can be made of a tight-weave fiberglass. Laterally-spaced corners of the diamond-shaped patterns include connection members that can be engaged to affix the strap and the air-permeable sheet around a duct. Various aspects include an air-impermeable air barrier surrounding the wide-weave fiberglass sheet and strap. The air barrier can include a window that directs air from a ruptured duct. Various aspects can be used on a bleed-air duct of an aircraft. The window of the air barrier can be aimed at a temperature sensor. A valve can close the bleed-air duct if the temperature sensor detects a high temperature leak.

A system for active control of radial gap around an annular row of rotor blades of a turbine engine, notably rotor blades of a low-pressure compressor of an aircraft turbojet engine. The system comprises an annular row of rotor blades; an outer casing around the annular row of rotor blades; a radial gap between the rotor blades and the outer casing; an oil circuit which is suitable for recovering the calories from a reduction gear box such as a planetary gear train which drives the fan. The oil circuit includes an expansion module which is configured to be expanded by the calories recovered from the oil. The expansion module is placed inside the outer casing so as to modulate its diameter around the rotor blades.

A method of fabricating a ceramic component includes hot pressing a composite component with a glass powder/filler cover mixture to form a consolidated glass-based coating on the composite component.

A propeller blade comprises a root, a tip distal from the root, a trailing edge extending from the root to the tip, a trailing edge, e.g. foam, insert, a shell forming an outer surface of the propeller blade and a plurality of stitches of yarn extending through two parts of the shell adjacent the trailing edge, wherein the yarns do not extend through the trailing edge insert.

The invention relates to a fan blade (3) of a turbomachine (15) comprising a structure (4) made of composite material having, within the root (5) and/or the stilt (6) of the blade, a first layer (11) comprising the lower face (16) and having a first thickness (E1) of between 10% and 25% of the total thickness (E), a second layer (12) comprising the suction face (17) and having a second thickness (E2) of between 10% and 25% of the total thickness (E), and a central layer (13) extending between the first layer (11) and the second layer (12), the shortening of the warp strands (9) in the first and second layers (11, 12) being greater than the shortening of the warp strands (9) in the central layer (13).

Tooling for manufacturing an air deflection cascade for a thrust reverser system of an aircraft nacelle includes a plurality of spars, each spar being connected to at least one adjacent spar by a plurality of deflection vanes. The tooling includes at least one molding bar and at least one molding column of a row of vanes, comprising two opposing lateral faces extending along the longitudinal direction of the tooling, and comprising molding cavities. The tooling includes a fixed structure on which the molding bar and the molding column are mounted. The fixed structure enabling a translational movement, along a transverse direction of the tooling, of the molding bar. The tooling includes a compression device to provide the compression of elements made of a composite material arranged in the tooling and intended to form at least one part of the cascade to be manufactured.

The invention relates to a fan blade (3) of a turbomachine (15) comprising a structure (4) made of composite material having, within the root (5) and/or the stilt (6) of the blade, a first layer (11) comprising the lower face (16) and having a first thickness (E1) of between 10% and 25% of the total thickness (E), a second layer (12) comprising the suction face (17) and having a second thickness (E2) of between 10% and 25% of the total thickness (E), and a central layer (13) extending between the first layer (11) and the second layer (12), the shortening of the warp strands (9) in the first and second layers (11, 12) being greater than the shortening of the warp strands (9) in the central layer (13).

An impeller for use with centrifugal compressors or pumps is provided and described along with methods for making such multi-component polymeric articles such as open or closed impellers and other assembled molded articles, which may optionally include openings therein. The impeller includes a composite comprising a matrix material selected from at least one thermoplastic polymer or at least one thermosetting polymer; and at least one continuous reinforcing fiber. The impeller includes at least one first flange comprising the composite, the first flange having an exterior surface and an interior surface, the first flange defining a first opening extending longitudinally therethrough; and at least one rib having a first end and a second end, the at least one rib positioned such that its first end engages the at least one first flange. Ring members and additional, second flanges, and optionally outer banding rings may be provided in various designs. The multi-component polymeric composite articles are formed of composite parts that are first molded, then assembled, positioned in a mold and remolded, optionally using removable cores for retaining openings within the remolded structures.

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 turbopump for a liquid rocket engine in which an oxidizer is pumped, where the turbopump is formed with a single piece rotor within a single piece housing by a metal additive manufacturing process, and where surfaces exposed to the oxidizer is coated with enamel glass to provide a smooth surface over the rough printed surface and to provide burn resistance to the base metal from exposure to the oxidizer such as oxygen. A Mondaloy coating can be used below the enamel glass coating to add additional burn resistance to the base metal.