Abstract: A method for manufacturing a part made of composite material for a turbomachine, in particular of an aircraft, includes the steps of: b) arranging a preform made of fibers in a mold, c) injecting polymerizable resin into the mold, d) machining the part, and e) visually checking the part. Step b) is preceded by a step a) in which at least one compliance coating is deposited in the mold. The compliance coating has a calibrated thickness (X) and at least one visual aspect identifiable by an operator. The coating is configured to cover at least one area of the preform and to be rigidly attached thereto by the resin at the end of step c) Step e) includes verifying, by the operator, the presence of the aspect in the area.

Abstract: A method for producing a part by injecting resin into a woven fiber preform includes the steps of (a) shaping the preform, (b) forming the preform, and (c) injecting resin into the preform. The step of injecting resin into the preform is carried out by means of equipment that includes a mold, a countermold, and resin injecting means. The step of injecting resin into the preform includes the substeps of: partially opening the equipment, injecting resin into the equipment, closing the equipment, and pressurizing and heating the impregnated preform between the mold and the countermold.

Abstract: A compacting and injection mold for a fiber preform is for use in fabricating a turbine engine guide vane out of composite material. The mold includes a shell forming a trough that is to receive the fiber preform and that is closed in leaktight manner by bottom and top covers, compacting blocks arranged inside the trough each having a surface pressing normally against a surface of the fiber preform that is to be compacted, and closure blocks arranged inside the trough. Each closure block has a surface pressing normally against a surface of a compacting block and does not have a surface in contact with the fiber preform.

Abstract: A compacting and injection mold for a fiber preform is for use in fabricating a turbine engine guide vane out of composite material. The mold includes a shell forming a trough that is to receive the fiber preform and that is closed in leaktight manner by bottom and top covers, compacting blocks arranged inside the trough each having a surface pressing normally against a surface of the fiber preform that is to be compacted, and closure blocks arranged inside the trough. Each closure block has a surface pressing normally against a surface of a compacting block and does not have a surface in contact with the fiber preform.

Abstract: A turbomachine casing including a substantially cylindrical wall and an annular one-piece acoustic insulation panel mounted inside the wall, the panel including an annular surface that is radially external opposite a radially internal annular surface of the wall, wherein the wall includes on its internal angular surface first projecting members which bear axially against second projecting members belonging to the external annular surface of the panel and which are fixed to these second members in a dismountable manner.

Abstract: A compacting and injection mold for a fiber preform is for use in fabricating a turbine engine guide vane out of composite material. The mold includes a shell forming a trough that is to receive the fiber preform and that is closed in leaktight manner by bottom and top covers, compacting blocks arranged inside the trough each having a surface pressing normally against a surface of the fiber preform that is to be compacted, and closure blocks arranged inside the trough. Each closure block has a surface pressing normally against a surface of a compacting block and does not have a surface in contact with the fiber preform.

Abstract: A turbine engine casing, including a substantially cylindrical wall and a single-piece annular panel for acoustic insulation mounted radially inside the wall, is provided. The panel includes a radially outer annular surface fitted with upstream and downstream first projecting members respectively arranged in the upstream and downstream portions of the radially outer annular surface of the panel. The wall includes a radially inner annular surface fitted with upstream and downstream second projecting members that are releasably fastened respectively to the upstream and downstream first projecting members.

Abstract: A device for fabricating a composite material part by injecting resin into a fiber structure. The device includes: a first die presenting two adjacent support surfaces defining a reentrant angle between them; at least one chock with a wedge-shaped portion configured to press the fiber structure into the angle; and a second die movable relative to the first die, the first and second dies being configured to clamp on the fiber structure and the chock. The chock is connected to the second die by at least one link, the link being hinged relative to the second die and relative to the chock to guide the wedge-shaped portion towards the angle to press the fiber structure into the angle when the second die approaches the first die.

Abstract: A device for manufacturing a fan casing of a turbomachine made of composite material, in which a mold includes a cylindrical body of lengthways axis and side flanges, and in which a counter-mold includes a cylindrical body and side counter-flanges. The counter-flanges are configured to be attached securely to the flanges, the body of the mold and the body of the counter-mold are concentric, the preform is configured to be positioned between the body of the mold and the body of the counter-mold, and the material of the body of the mold has an appreciably higher expansion coefficient than that of the body of the counter-mold.

Abstract: The invention relates to a turbine engine, such as an aircraft turbofan or a turboprop engine, including a fan casing (10) having a substantially cylindrical wall (12) surrounding the blades of the fan, and at least two annular acoustic insulation panels (18, 20) mounted radially inside said wall (12), a first panel (18) being mounted upstream of the fan, a second panel (20) being located downstream of the first panel (18) and supporting an inner layer (42) of abradable material located opposite the radially outer ends of the blades of the fan, characterised in that the two annular panels (18, 20) form a single structural unit.

Abstract: A turbomachine casing including a substantially cylindrical wall and an annular one-piece acoustic insulation panel mounted inside the wall, the panel including an annular surface that is radially external opposite a radially internal annular surface of the wall, wherein the wall includes on its internal angular surface first projecting members which bear axially against second projecting members belonging to the external annular surface of the panel and which are fixed to these second members in a dismountable manner.

Abstract: The invention relates to a turbine engine casing comprising a substantially cylindrical wall (12) and a single-piece annular panel (18) for acoustic insulation mounted radially inside the wall (12), the panel (18) including a radially outer annular surface (36) fitted with upstream and downstream first projecting members (70) respectively arranged in the upstream and downstream portions of the radially outer annular surface (36) of the panel (18), the wall (12) including a radially inner annular surface fitted with upstream and downstream second projecting members (80) that are releasably fastened respectively to the upstream and downstream first projecting members (70).

Abstract: A device for fabricating a composite material part by injecting resin into a fiber structure. The device includes: a first die presenting two adjacent support surfaces defining a reentrant angle between them; at least one chock with a wedge-shaped portion configured to press the fiber structure into the angle; and a second die movable relative to the first die, the first and second dies being configured to clamp on the fiber structure and the chock. The chock is connected to the second die by at least one link, the link being hinged relative to the second die and relative to the chock to guide the wedge-shaped portion towards the angle to press the fiber structure into the angle when the second die approaches the first die.

Abstract: A compacting and injection mold for a fiber preform is for use in fabricating a turbine engine guide vane out of composite material. The mold includes a shell forming a trough that is to receive the fiber preform and that is closed in leaktight manner by bottom and top covers, compacting blocks arranged inside the trough each having a surface pressing normally against a surface of the fiber preform that is to be compacted, and closure blocks arranged inside the trough. Each closure block has a surface pressing normally against a surface of a compacting block and does not have a surface in contact with the fiber preform.

Abstract: A device for suctioning a liquid contained in a vessel, that includes a take-up tube that is received in the vessel such that a bottom end of the section is submerged in the liquid. The bottom end of the take-up tube is extended downward by a rotationally symmetrical tip which has a main substantially vertical axis open downward and which includes an outer radial collar.

Abstract: A one-piece soundproofing panel which is attached within an circumferential air blower casing of a turbomachine, with an axis, in which circulates an airflow from upstream to downstream, is disclosed. The panel includes a circumferential rigid seat with a longitudinal cylindrical part, arranged to axially extend with respect to the axis A of the turbomachine, having an outside surface, intended to come to extend facing with an internal surface of the air blower casing, and an internal surface to which is applied a soundproofing coating; and an annular fastening flange, formed at the upstream end of the longitudinal cylindrical part, radially outwardly extending, the fastening flange being arranged to cooperate with a fastening flange of the air blower casing.

Abstract: A device for manufacturing a fan casing of a turbomachine made of composite material, in which a mold includes a cylindrical body of lengthways axis and side flanges, and in which a counter-mold includes a cylindrical body and side counter-flanges. The counter-flanges are configured to be attached securely to the flanges, the body of the mold and the body of the counter-mold are concentric, the preform is configured to be positioned between the body of the mold and the body of the counter-mold, and the material of the body of the mold has an appreciably higher expansion coefficient than that of the body of the counter-mold.

Abstract: One-piece soundproofing panel intended to be attached within an circumferential air blower casing of a turbomachine, comprising an axis, in which circulates an airflow from upstream to downstream, the panel including a circumferential rigid seat comprising a longitudinal cylindrical part, arranged to axially extend with respect to the axis A of the turbomachine, comprising an outside surface, intended to come to extend facing with an internal surface of the air blower casing, and an internal surface to which is applied a soundproofing coating and an annular fastening flange, formed at the upstream end of the longitudinal cylindrical part, radially outwardly extending, the fastening flange being arranged to cooperate with a fastening flange of the air blower casing.