A fan blade comprises interleaved plies, where interleaving comprises distributing wide plies within narrow plies and short plies within long plies in the fan blade; wherein the interleaving is defined as an actual intersection of a plurality of plies of different variable dimensions that extend in the chordwise direction with another plurality of plies of different variable dimensions that extend in the spanwise direction such that their respective longitudinal axes intersect with one another at angles of 5 to 175 degrees.

A method for forming a ceramic matrix composite component includes forming a fibrous preform of the component with a plurality of fiber layers and a fill region disposed between one or more of the plurality of fiber layers. Ceramic particles are provided in the fill region, which is densified using chemical vapor infiltration.

A fiber-reinforced component for use in a gas turbine engine includes a first braided fiber sleeve forming a cooling channel and a plurality of fiber plies enclosing the first braided fiber sleeve, with the plurality of fiber plies forming first and second walls separated by the first braided fiber sleeve. The fiber-reinforced component further includes a matrix material between fibers of the braided fiber sleeve and the plurality of fiber plies.

The present invention relates to a blade (7) comprising: —a composite material structure (17), —a blade root fastening portion (9) further comprising a shoulder (10) extending into the recess from the wall—a base (18) arranged in the recess and comprising a support member configured to abut against the shoulder (10) of the blade root fastening portion (9) and a passage (39) formed in the support member, the sections (23) of the blade root portion (22) of the composite material structure extending through the passage (39), and—a blocking part (19) arranged in the recess between the two sections (23) of the blade root portion (22) such that each section of the blade root portion (23) is pressed against the support member by the blocking part (19).

Disclosed herein is an article comprising a first group of plies having a number of plies N.sub.1 each having unidirectional tows oriented in a first direction β.sub.1 and a second group of plies having a number of plies N.sub.2 each having unidirectional tows oriented in a second direction β.sub.2; where β.sub.1 is not equal to β.sub.2; wherein N.sub.1 and N.sub.2 are both integer numbers. At least one of the first group of plies or the second group of plies has at least one tow of different thickness from another tow, has a different tow spacing from another tow spacing, or a combination thereof.

A vane arc segment includes an airfoil piece that defines first and second platforms and a airfoil section that extends between the first and second platforms. The airfoil section has a trailing edge, a leading edge, a pressure side, and a suction side. The platforms each define first and second circumferential mate faces, forward and aft sides, a gaspath side, a non-gaspath side, and a radial flange that projects from the non-gaspath side. Each radial flange extends continuously and includes a first leg portion that extends adjacent the trailing edge, a second leg portion that extends from the first leg portion and curves around the suction side, and a third leg portion that extends from the second leg portion toward the forward side.

The invention provides a fitted platform (1) for positioning between two adjacent blades of an aviation turbine engine fan, said platform comprising a flow passage wall (10) made of composite material having a central portion (16) and first and second margins (18) each extending in a longitudinal direction of said wall, each margin extending over a determined distance (D) from the central portion (16) in a transverse direction of said wall, said flow passage wall comprising fiber reinforcement densified by a matrix, the platform being characterized in that the fiber reinforcement present in the central portion (16) presents three-dimensional weaving, and in that the fiber reinforcement present in the first and second margins (18) presents two-dimensional weaving, at least in part. The invention also provides a fan module, a turbine engine, and a method of fabricating such a platform.

A fan casing for an engine having a fan with fan blades that each have a centre of gravity (CoG) that lies on a fan blade CoG plane, the fan casing having a central axis and comprising a main impact region comprising carbon-fibre reinforced polymer (CFRP) blocks and glass-fibre reinforced polymer (GFRP) blocks having a constant thickness throughout the axial extent of the main impact region, wherein the total depth of the main impact region is equal to the sum of the thicknesses of the CFRP blocks and GFRP blocks, each of the GFRP blocks is positioned between two CFRP blocks, and the thickness of at least one of the GFRP blocks is different to the thickness of another of the GFRP blocks.

The invention relates to a method for producing a grid made of composite material for straightening an air flow for an aircraft turbine engine. The described method is based on the use of longitudinal members (301) which have recesses (303) to allow the penetration of connecting elements (304) into said recesses during the manufacture of the grid.

An assembly for a gas turbine engine according to an example of the present disclosure includes at least one platform having a main body extending between a first mate face and a second mate face to establish a gas path surface. The main body has an internal passage extending circumferentially between a first opening along the first mate face and a second opening along the second mate face relative to an assembly axis. A perimeter of the first mate face establishes a first area, a perimeter of the second opening establishes a second area, and the second area is greater than the first area. An airfoil section extends radially from the at least one platform.