摘要:
A composite material casing of varying thickness, in particular for a gas turbine fan, is made by forming fiber reinforcement and densifying the reinforcement with a matrix. The fiber reinforcement is made by winding superposed layers of a fiber texture onto a mandrel, the texture being made by three-dimensional weaving with varying thickness.
摘要:
A composite material casing of varying thickness, in particular for a gas turbine fan, is made by forming fiber reinforcement and densifying the reinforcement with a matrix. The fiber reinforcement is made by winding superposed layers of a fiber texture onto a mandrel, the texture being made by three-dimensional weaving with varying thickness.
摘要:
A coupling made of composite material including a polymer matrix reinforced by a fiber structure is disclosed. The coupling includes a structural portion reinforced by a main fiber structure, and a first machining portion reinforced by a first fiber structure that is distinct from the main fiber structure. The matrices of the structural portion and of the first machining portion are identical. The first machining portion is situated on at least a fraction of the main face of the structural portion and is machined in a first machining surface, and there is no intersection between the first machining surface and the fibers of the main fiber structure.
摘要:
A panel for supporting abradable material in a turbojet, the panel comprising a rigid support for fastening to an inside wall of a fan casing and having one face covered in a laminated structure carrying a layer of abradable material, the laminated structure comprising sheets of fibers embedded in a polymer, and comprising an upstream portion covered by the abradable material and a downstream portion that extends beyond the abradable material, the thickness of the downstream portion being greater than the thickness of the upstream portion and being capable of withstanding ice impacts.
摘要:
The invention relates to a coupling made of composite material comprising a polymer matrix reinforced by a fiber structure. The coupling comprises a structural portion reinforced by a main fiber structure, and a first machining portion reinforced by a first fiber structure that is distinct from the main fiber structure, the matrices of the structural portion and of the first machining portion being identical, the first machining portion being situated on at least a fraction of the main face of the structural portion and being machined in a first machining surface, there being no intersection between the first machining surface and the fibers of the main fiber structure.
摘要:
The relief device is designed to divert a portion of a main flow toward a by-pass flow in a turbojet that includes a main flow stream, a by-pass flow stream and an intermediate casing. The relief device includes inner openings of the inner shroud, outer openings of the outer shroud, a relief circuit connecting the inner openings to the outer openings, and a blanking device capable of opening and closing the relief circuit. The relief circuit includes upstream holes of the intermediate casing, downstream holes of the intermediate casing, and an annular channel defined between the intermediate casing, the outer shroud and a connecting partition. The connecting partition rests on the intermediate casing so as to encompass the downstream holes of the intermediate casing in the annular channel and resting on the outer shroud so as to encompass the outer openings of the outer shroud in the annular channel.
摘要:
The relief device is designed to divert a portion (94) of a main flow (90) toward a by-pass flow (92) in a turbojet that comprises a main flow stream (10), a by-pass flow stream (14) and an intermediate casing (20).The relief device comprises: inner openings (26) of the inner shroud (16), outer openings (28) of the outer shroud (18), a relief circuit (32, 34, 36, 52, 56) connecting said inner openings (26) to said outer openings (28), blanking means (58, 60, 62, 64, 66) capable of opening and closing said relief circuit and wherein the relief circuit (32, 34, 36, 52, 56) comprises upstream holes (32) of the intermediate casing (20), downstream holes (34) of the intermediate casing (20), an annular channel (52) defined between the intermediate casing (20), the outer shroud (18) and a connecting partition (54), said connecting partition (54) resting on the intermediate casing (20) so as to encompass the downstream holes (34) of the latter in said annular channel (52) and resting on the outer shroud (18) so as to encompass the outer openings (28) of the latter in said annular channel (52).
摘要:
The de-icing device is intended for the vane (10) of the inlet guide wheel (4) of a turbojet (2), comprising a fixed part (12) arranged on the upstream side and a mobile flap (18) arranged on the downstream side, in which said fixed part (12) comprises a trailing edge (16) substantially in the shape of a “U”, with one of the branches (162) being located on the intrados side (I) and the other branch (164) being located on the extrados side (E). It comprises at least one emission window (202), oriented substantially along an upstream-downstream direction, and arranged along the branch (162) of the “U” located on the intrados side (I) of the trailing edge (16).The inlet guide wheel (4) vane (10) is equipped with at least such a de-icing device.The aircraft engine (2) comprises at least one vane (10) equipped with such a de-icing device.
摘要:
A rotor of a turbomachine, such as a multi-flow turbojet engine fan, has a disc including, on the rim thereof, substantially axial slots with a dovetailed cross-section, and blades mounted individually in the slots, an axial wedge positioned between the root of the blades and the bottom of the slots, and a transverse lock providing upstream axial immobilization of the blades in the slot thereof. The lock is guided in radial notches formed in the flanks of the slots and radially supported against the wedge. The axial wedge is immobilised in the upstream direction, butting up against a transverse annular component secured to the disc.
摘要:
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.