Abstract: A device for moulding at least one bladed part of a turbine engine, including a base; a mould formed from a plurality of parts nested inside one another, this mould being applied to the base. A first seal is mounted between the mould and the base; and a bell is mounted on the mould and around the mould, this bell being applied to the base. A second seal is mounted between the bell and the base, this bell being configured to be held tight against the base and having interior surfaces engaging by wedge effect with complementary exterior surfaces of the mould in order to apply a clamping force on the parts of this mould.

Abstract: A device for shaping at least one fibrous preform of a bladed part of a turbine engine, the device including a mould formed of multiple parts nested inside one another, the mould defining an internal cavity for enclosing the preform entirely, the cavity having two platform zones and a blade zone extending between the two platform zones, wherein the mould includes at least a lower shell, an upper shell, a side shell, and end shells, and in that each of the side and end shells includes three elements, respectively lower, intermediate and upper.

Abstract: A mold for manufacturing a turbomachine fan casing made of composite material, includes a main axis mandrel around which a fibrous preform of a fan casing is intended to be wound; a plurality of counter-mold angular sectors assembled on the outer contour of the mandrel which are intended to close the mold and to compact the fibrous preform wound on the mandrel; wherein a flat seal with a main elongation axis directed along the main axis is arranged between each angular sector, the flat seal being compressed between two adjacent angular sectors, a first angular sector including a sealing portion passing below a lower face of the flat seal while a second angular sector including a sealing portion passing above an upper face of the flat seal.

Abstract: Methods for producing an annular casing for an aircraft turbine engine are provided. The annular casing includes an annular body made from a composite material based on a first resin, and a fire-resistant outer layer which covers an external annular surface of the body and which is made from a composite material based on a self-extinguishing second resin. The method includes preparing a strip of a glass fabric preimpregnated with said second resin, this strip including woven fibres oriented in directions that are perpendicular to one another and inclined by an angle of approximately 45° with respect to the axis of elongation of the strip, and applying the strip to the external surface of the body so as to cover the entirety of this surface in a single pass of the strip around the body.

Abstract: Method for producing a casing made of a composite material for an aircraft turbine engine, the casing having an annular shape and including an annular fibrous preform formed by winding a fibrous cloth soaked in a polymer matrix, the method including the steps of: a) positioning an edge of the cloth on a molding drum, this cloth having a generally elongate shape and the edge being located at a first longitudinal end of the cloth, b) winding the cloth on the drum, over at least one rotation, so as to obtain the preform wound around the drum, c) molding of the preform and hardening of the resin which is injected into the preform or pre-impregnated on the preform, wherein the method includes, before step a), a step i) of mounting a removable stop on the drum, and in that step a) includes abutting the edge against this stop.

Abstract: A mould for manufacturing a turbomachine fan casing made of a composite material with fibrous reinforcement that is densified by a matrix, includes an impregnation mandrel around which a fibrous preform is to be wound and angular counter-mould sectors assembled around the external contour of the impregnation mandrel, which are intended to close the mould. The impregnation mandrel includes a main body with an annular shape, and an annular barrel which is arranged around the main body and around which the fibrous preform is to be wound, the barrel and the angular sectors defining a moulding cavity intended to receive the fibrous preform. The main body and the angular sectors are made of a first material having a first thermal expansion coefficient, the barrel being made of a second material that has a second thermal expansion coefficient, the second thermal expansion coefficient being greater than the first thermal expansion coefficient.

Abstract: A tooling for injecting a polymer resin into a fibrous preform for the manufacture of a revolution part in composite material including a barrel shape with an inside diameter of smaller diameter delimiting the revolution part into an upstream portion and a downstream portion of the inside diameter, the upstream portion including a back-draft intermediate portion, injection tooling wherein, to allow a demolding of the barrel-shaped part once the injection and the polymerization of the polymer resin are carried out, the injection tooling includes on the one hand a frustoconical drum comprising a first drum portion in direct contact with an inner surface of the portion of the revolution part downstream of the inside diameter and a second drum portion and on the other hand a segmented insert whose outer surface matches an inner surface of the portion of the revolution part upstream of the inside diameter.

Abstract: An injection mold for the manufacture of an axisymmetric part of composite material including a mandrel supporting a fibrous preform and including an annular wall, and a plurality of counter-mold angular sectors assembled on the mandrel and intended to close the mold and to compact the fibrous preform wound on the mandrel. Each angular sector includes an annular base intended to come into contact with the fibrous preform. The annular base extends between the first and second lateral edges in a circumferential direction, the first lateral edge of the annular base of an angular sector being in contact with a second lateral edge of the annular base of an adjacent angular sector.

Abstract: A mold for manufacturing a turbomachine fan casing of composite material, includes a mandrel around which a fibrous preform of the fan casing is to be wound; counter-mold angular sectors assembled on the external contour of the mandrel which are intended to close the mold and to compact the fibrous preform wound on the mandrel; wherein each angular sector includes a first lateral flange positioned at the first end of the angular sectors and a second lateral flange positioned at a second end of the angular sectors, the first and second lateral flanges cooperating respectively with the second and first lateral flanges of the adjacent angular sectors. An angular sector includes a first groove formed in the first of second lateral flange, a first seal being positioned in the first groove, the first seal to be compressed between the first and second lateral flanges of two adjacent angular sectors.

Abstract: A mold for manufacturing a turbomachine fan casing made of composite material, includes a main axis mandrel around which a fibrous preform of a fan casing is intended to be wound; a plurality of counter-mold angular sectors assembled on the outer contour of the mandrel which are intended to close the mold and to compact the fibrous preform wound on the mandrel; wherein a flat seal with a main elongation axis directed along the main axis is arranged between each angular sector, the flat seal being compressed between two adjacent angular sectors, a first angular sector including a sealing portion passing below a lower face of the flat seal while a second angular sector including a sealing portion passing above an upper face of the flat seal.

Abstract: A method for closing an injection mold for manufacturing a revolution part made of composite material, the mold including a mandrel supporting a fiber preform and angular sectors comprising an annular base to come into contact with the fiber texture, the annular base extending between first and second side edges along a circumferential direction. The method includes successive positioning and fixing the angular sectors on the mandrel, the annular base of each sector compacting the fiber preform portion present oppositely, the side edges of the annular base of each angular sector being in contact with the side edges of the annular base of the adjacent sectors. Before the positioning and fixing of the angular sectors on the mandrel, strip s are placed on the exposed surface of the fiber preform, each strip covering an area of the fiber preform located facing a junction area between two adjacent angular sectors.

Abstract: A device for shaping at least one fibrous preform for producing a bladed part of a turbomachine, this device including a mould formed by several parts that are interlocked with each other, this mould defining at least one internal cavity configured to receive the preform and to enclose the preform integrally, this cavity being intended to have two platform areas and a blade area extending between the two platform areas, wherein the mould includes at least a lower shell, an upper shell, a side shell, and end shells, and in that each of the side and end shells includes three elements, respectively lower, intermediate and upper.

Abstract: A device for moulding at least one bladed part of a turbomachine, including a base, a mould formed from several parts that are interlocked with each other, this mould being applied to the base and first sealing means being mounted between the mould and the base, a bell-shaped dome mounted on the mould and around the mould, this bell-shaped dome being applied to the base and second sealing means being mounted between the bell-shaped dome and the base, this bell-shaped dome being configured to be held clamped against the base and including inner surfaces cooperating by corner effect with complementary outer surfaces of the mould in order to apply a clamping force on the parts of this mould.

Abstract: Methods for producing an annular casing for an aircraft turbine engine are provided. The annular casing includes an annular body made from a composite material based on a first resin, and a fire-resistant outer layer which covers an external annular surface of the body and which is made from a composite material based on a self-extinguishing second resin. The method includes preparing a strip of a glass fabric preimpregnated with said second resin, this strip including woven fibres oriented in directions that are perpendicular to one another and inclined by an angle of approximately 45° with respect to the axis of elongation of the strip, and applying the strip to the external surface of the body so as to cover the entirety of this surface in a single pass of the strip around the body.

Abstract: An installation for forming a fiber preform, includes a follower roller. The follower roller presents a profile in section that has at least a first slope forming an angle with the axis of the follower roller and a second slope forming a second angle with the axis of the follower roller that is different from the first angle. The installation also has at least one backing roller presenting a shape complementary to the first and second slopes, the installation including a holder for holding each backing roller and configured to hold the backing roller at a predetermined distance from the first and second slopes or configured to apply contact pressure from the backing roller against the first and second slopes.

Abstract: The invention relates to a method for manufacturing a carrying casing (12) provided with a collar (18) for supporting at least one cartridge of abradable material for a turbomachine, said carrying casing (12) comprising at least one bare annular casing (16) and one block of honeycomb material (20) that comprises an outer face (22) configured to be secured to an inner face (24) of said bare annular casing (16), said block being covered with a skin (26), characterized in that it comprises successively: —a step in which the outer face (22) of the block (20) is secured to the inner face (24) of the bare annular casing (16), —a step in which the circularity of San inner face (32) of the block (20) is monitored and in which, if necessary, the inner face (32) of the block (20) is machined to round, —a step in which, simultaneously, said skin (26) is produced and is secured to said block (20).

Abstract: An injection mold for the manufacture of an axisymmetric part of composite material including a mandrel supporting a fibrous preform and including an annular wall, and a plurality of counter-mold angular sectors assembled on the mandrel and intended to close the mold and to compact the fibrous preform wound on the mandrel. Each angular sector includes an annular base intended to come into contact with the fibrous preform. The annular base extends between the first and second lateral edges in a circumferential direction, the first lateral edge of the annular base of an angular sector being in contact with a second lateral edge of the annular base of an adjacent angular sector.

Abstract: A process for shaping a fibrous preform includes the insertion of each attachment tab of a fibrous texture into a corresponding aperture of an impregnation mandrel, the attachment by a removable retaining device of each tab inserted into each aperture against a surface of the impregnation mandrel, the winding under tension of the fibrous texture on the impregnation mandrel in order to obtain a fibrous preform.

Abstract: A method of fabricating a composite material casing of varying thickness for a gas turbine includes using three-dimensional or multilayer weaving to make a fiber texture in the form of a strip; winding the fiber texture as a plurality of superposed layers onto a mandrel of profile corresponding to the profile of the casing to be fabricated, so as to obtain a fiber preform of shape corresponding to the shape of the casing to be fabricated; and densifying the fiber preform with a matrix. During winding of the fiber texture on the mandrel, a textile strip is interposed between the adjacent turns of the fiber texture, the textile strip presenting a width that is less than the width of the fiber texture and defining a retention zone of the casing.

Abstract: A method of fabricating a textile structure of varying thickness including using a loom to weave a fiber texture in the form of a strip extending lengthwise along a longitudinal axis and widthwise along an axis perpendicular to the longitudinal axis, and causing the texture to be wound under tension onto a mandrel. The texture includes a portion presenting extra thickness. During the winding of the texture, a spacer element is interposed between adjacent turns of the fiber texture onto the mandrel. Each spacer element extends in the width direction of the texture over a portion thereof situated outside the portion of extra thickness and presenting, over the portion of the texture situated outside the portion of extra thickness, a thickness that corresponds at least to the difference between thicknesses of the portion of extra thickness and of the portion of the texture situated outside the portion of extra thickness.