Abstract: A method for manufacturing a casing, for example, an exhaust casing, for a turbomachine. The method generally includes: (a) producing casing sectors, each casing sector having a hub sector, a ferrule sector, and at least one arm linking the hub and ferrule sectors, (b) arranging the casing sectors adjacently and circumferentially, such that each hub sector has longitudinal edges facing longitudinal edges of adjacent hub sectors, (c) welding the longitudinal edges facing the hub sectors, and (d) adding and welding at least a second part of the ferrule to the casing sectors.

Abstract: A casing is provided, for example, an exhaust casing for a turbomachine. The casing generally includes an inner hub having an axis of rotation and an outer annular ferrule extending around the hub, the ferrule configured to define, with the hub, an annular flow path for a gas stream. In some examples, the ferrule is rigidly connected to the hub by arms. The hub generally includes, at one longitudinal end, a scalloped annular flange comprising solid portions distributed at regular intervals about said axis and spaced apart from each other by hollow portions. The hub is produced by assembling several angular hub sectors arranged circumferentially end to end around the axis, each hub sector connected to an adjacent hub sector by a longitudinal weld bead that extends over substantially the entire axial extent of the hub and that is substantially aligned axially with a hollow portion of said flange.

Abstract: The invention relates to an assembly comprising: a turbomachine exhaust case (110) that includes an external sleeve and an internal sleeve inside the former, both sleeves extending concentrically about a turbomachine axis, and also includes a plurality of arms extending radially between the sleeves; and an annular part (130) that is centered about the axis, is mounted on one sleeve of the exhaust case, and is located downstream of the exhaust case in the direction in which the air flows inside the turbomachine; the assembly is characterized in that the annular part and the sleeve of the exhaust case on which the annular part is mounted each have a circumferential thread (131, 115), said threads cooperating with each other in order to allow the annular part to be screwed onto the sleeve of the exhaust case.

Abstract: A method for manufacturing a casing, for example, an exhaust casing, for a turbomachine. The method generally includes: (a) producing casing sectors, each casing sector having a hub sector, a ferrule sector, and at least one arm linking the hub and ferrule sectors, (b) arranging the casing sectors adjacently and circumferentially, such that each hub sector has longitudinal edges facing longitudinal edges of adjacent hub sectors, (c) welding the longitudinal edges facing the hub sectors, and (d) adding and welding at least a second part of the ferrule to the casing sectors.

Abstract: A casing is provided, for example, an exhaust casing for a turbomachine. The casing generally includes an inner hub having an axis of rotation and an outer annular ferrule extending around the hub, the ferrule configured to define, with the hub, an annular flow path for a gas stream. In some examples, the ferrule is rigidly connected to the hub by arms. The hub generally includes, at one longitudinal end, a scalloped annular flange comprising solid portions distributed at regular intervals about said axis and spaced apart from each other by hollow portions. The hub is produced by assembling several angular hub sectors arranged circumferentially end to end around the axis, each hub sector connected to an adjacent hub sector by a longitudinal weld bead that extends over substantially the entire axial extent of the hub and that is substantially aligned axially with a hollow portion of said flange.

Abstract: An exhaust casing of a turbine engine for an aircraft which extends along an axis and includes: a central hub, an annular outer shroud and arms which connect the central hub to the outer shroud, at least one yoke for attaching the exhaust casing to the turbine engine being located on the outer shroud and forming at least one lug extending in a plane perpendicular to the axis and protruding toward the exterior of the outer shroud. The outer shroud includes ribs which form a constant excess of the outer shroud, which are located on either side of the at least one lug of the at least one yoke, and which are aligned with the at least one lug.

Abstract: The invention relates to a fairing (37) for a mixer (28) of a nozzle (26) of a dual-flow turbomachine (20), said mixer being of an overall annular shape and extending along a longitudinal axis (24) of the turbomachine, said mixer comprising an upstream part (29) provided with a flange (31) extending radially toward the outside of the mixer, intended to be fastened to an exhaust casing (21) of the turbomachine, and a downstream part (33) forming a flow mixing area, the fairing (37) being of an overall annular shape and configured to extend around the upstream part (29) of the mixer (28) and to be attached to the flange (31) of said upstream part (29), the fairing being without means for fastening to the downstream part (33) of the mixer (28), in such a way as to connect the fairing (37) to the mixer (28) at a distance from the flow mixing area.

Abstract: The present invention relates to a turbine engine casing (1), in particular a turbojet exhaust casing, including at least one hoop (2) and at least one flange (3, 4) at least partially defining one end of said hoop (2), and at least one cap (5) positioned at least partially on the outer surface of the hoop (2), said cap (5) including a bore (6) capable of receiving an element for fastening the casing (1) to a bracket, the flange including an access cut-out (7a) substantially coaxial with the bore (6) of said at least one cap (5), said access cut-out (7a) enabling access to the bore (6), the access cut-out (7a) being provided at a release cut-out (7b) which is wider than the flange (3, 4) and constitutes a recess on said release cut-out (7b). The invention also relates to a turbine engine including a casing (1) and to a method for machining the latter according to the present invention.

Abstract: The invention relates to an assembly comprising: a turbomachine exhaust case (110) that includes an external sleeve and an internal sleeve inside the former, both sleeves extending concentrically about a turbomachine axis, and also includes a plurality of arms extending radially between the sleeves; and an annular part (130) that is centered about the axis, is mounted on one sleeve of the exhaust case, and is located downstream of the exhaust case in the direction in which the air flows inside the turbo-machine; the assembly is characterized in that the annular part and the sleeve of the exhaust case on which the annular part is mounted each have a circumferential thread (131, 115), said threads cooperating with each other in order to allow the annular part to be screwed onto the sleeve of the exhaust case.

Abstract: The invention relates to a turbomachine bearing support (1) supporting at least one bearing and extending according to a longitudinal principal axis of the turbomachine and comprising: a truncated part (11) having a diameter increasing from upstream to downstream; a flange part (12) which extends from the truncated part (11) as far as the bearing (5, 6) to which it is fixed by an axial flange (121), and having at its downstream end a radial internal flange (17) fixed to an oil inlet cover defining with the bearing (5, 6) an oil inlet container (170); oiled air clearance ducts (71) projecting downstream relative to the flange part (12) and on the oil inlet container (170) and to the other side upstream of the flange part (12) directly radially externally relative to the axial flange (121).

Abstract: A bypass engine bearing holder (1) that holds an upstream bearing (6) and defines, with said upstream bearing, an oil chamber (100) and an air chamber (200), comprising a frusto-conical portion (11) defining an upstream bearing chamber (160) and a downstream inner chamber (150), and includes an outer collar (13) connected, by a weld (135), to a flange (15) that extends outward from the frusto-conical portion (11). The outer collar (13) has a sealable gimlet (131) engaging with the upstream bearing (6) such as to seal the oil chamber (100). The bearing holder (1) includes a plurality of oil recovery ducts (8) leading to the downstream inner chamber (150) and to the upstream bearing chamber (160). The oil recovery ducts (8) lead to the upstream bearing chamber (160), downstream from the weld (135) of the outer collar (13) on the flange (15), the weld (135) of the outer collar (13) being axisymmetric.

Abstract: The invention relates to an exhaust casing (10) of a turbine engine for an aircraft which extends along an axis and which comprises a central hub (20), an annular outer shroud (30) and arms (40) which connect the central hub (20) to the outer shroud (30), at least one yoke (50) for attaching the exhaust casing (10) to the turbine engine being located on the outer shroud (30) and forming at least one lug (51) extending in a plane perpendicular to the axis and protruding toward the exterior of said outer shroud (30), characterized in that the outer shroud (30) comprises ribs (60) which form a constant excess of said outer shroud (30), which are located on either side of said at least one lug (51) of said at least one yoke (50), and which are aligned with said at least one lug (51).

Abstract: An assembly including an exhaust casing and an exhaust cone for a gas turbine engine, each including an axial annular flange, the two flanges being inserted into one another, one being radially external and the other radially internal, and held together by a mechanical attachment, and the assembly further including a guide by which, during operation of assembling the annular flanges to each other, the exhaust cone is in a predetermined angular position relative to the exhaust casing.

Abstract: The invention relates to a turbine engine exhaust casing (1), characterized in that it comprises: a hub (2), an outer ring (3); a plurality of structural arms (10) arranged circumferentially between the hub (2) and the outer ring (3); a stiffener (11) extending along at least a portion of the inner circumference of the hub (2), the hub (2) comprising at least one discharge hole (15), and the stiffener (11) comprising at least one discharge slot (16), so as to enable the discharge of a fluid from the casing (1). The invention also relates to a turbine engine comprising such an exhaust casing.

Abstract: The present invention relates to a bypass engine bearing holder (1) that holds an upstream bearing (6) and defines, with said upstream bearing, an oil chamber (100) and an air chamber (200), comprising a frusto-conical portion (11) defining an upstream bearing chamber (160) and a downstream inner chamber (150), and comprises an outer collar (13) connected, by a weld (135), to a flange (15) that extends outward from the frusto-conical portion (11). The outer collar (13) has a sealable gimlet (131) engaging with the upstream bearing (6) such as to seal the oil chamber (100). The bearing holder (1) comprises a plurality of oil recovery ducts (8) leading to the downstream inner chamber (150) and to the upstream bearing chamber (160). The oil recovery ducts (8) lead to the upstream bearing chamber (160), downstream from the weld (135) of the outer collar (13) on the flange (15), the weld (135) of the outer collar (13) being axisymmetric.

Abstract: The present invention relates to a turbine engine casing (1), in particular a turbojet exhaust casing, including at least one hoop (2) and at least one flange (3, 4) at least partially defining one end of said hoop (2), and at least one cap (5) positioned at least partially on the outer surface of the hoop (2), said cap (5) including a bore (6) capable of receiving an element for fastening the casing (1) to a bracket, the flange including an access cut-out (7a) substantially coaxial with the bore (6) of said at least one cap (5), said access cut-out (7a) enabling access to the bore (6), the access cut-out (7a) being provided at a release cut-out (7b) which is wider than the flange (3, 4) and constitutes a recess on said release cut-out (7b). The invention also relates to a turbine engine including a casing (1) and to a method for machining the latter according to the present invention.

Abstract: The invention relates to a fairing (37) for a mixer (28) of a nozzle (26) of a dual-flow turbomachine (20), said mixer being of an overall annular shape and extending along a longitudinal axis (24) of the turbomachine, said mixer comprising an upstream part (29) provided with a flange (31) extending radially toward the outside of the mixer, intended to be fastened to an exhaust casing (21) of the turbomachine, and a downstream part (33) forming a flow mixing area, the fairing (37) being of an overall annular shape and configured to extend around the upstream part (29) of the mixer (28) and to be attached to the flange (31) of said upstream part (29), the fairing being without means for fastening to the downstream part (33) of the mixer (28), in such a way as to connect the fairing (37) to the mixer (28) at a distance from the flow mixing area.

Abstract: An assembly including an exhaust casing and an exhaust cone for a gas turbine engine, each including an axial annular flange, the two flanges being inserted into one another, one being radially external and the other radially internal, and held together by a mechanical attachment, and the assembly further including a guide by which, during operation of assembling the annular flanges to each other, the exhaust cone is in a predetermined angular position relative to the exhaust casing.

Abstract: The invention relates to a turbomachine bearing support (1) supporting at least one bearing and extending according to a longitudinal principal axis of the turbomachine and comprising: a truncated part (11) having a diameter increasing from upstream to downstream; a flange part (12) which extends from the truncated part (11) as far as the bearing (5, 6) to which it is fixed by an axial flange (121), and having at its downstream end a radial internal flange (17) fixed to an oil inlet cover defining with the bearing (5, 6) an oil inlet container (170); oiled air clearance ducts (71) projecting downstream relative to the flange part (12) and on the oil inlet container (170) and to the other side upstream of the flange part (12) directly radially externally relative to the axial flange (121).

Abstract: The invention relates to a turbine engine exhaust casing (1), characterised in that it comprises: a hub (2), an outer ring (3); a plurality of structural arms (10) arranged circumferentially between the hub (2) and the outer ring (3); a stiffener (11) extending along at least a portion of the inner circumference of the hub (2), the hub (2) comprising at least one discharge hole (15), and the stiffener (11) comprising at least one discharge slot (16), so as to enable the discharge of a fluid from the casing (1). The invention also relates to a turbine engine comprising such an exhaust casing.