Abstract: The invention relates to a concentric gas flow mixer in a multiple-flow turbomachine, comprising a nominally cylindrical upstream part and a downstream part having outer and inner lobes distributed peripherally around the tower of said mixer, characterised in that it comprises at least one modified lobe having a wall thickness, in at least one area, which is different from the other lobes, so as to modify the vibratory response of said mixer.

Abstract: A device for attaching manifolds for cooling the casing of a preferably low-pressure turbine of a turbine engine by air jets. The device includes a mounting for the manifolds, shaped such as to keep the manifolds spaced apart from one another. A plurality of elements support the manifold mounting, each supporting element being attached to the casing, and connected to the manifold mounting by a connector. The device includes N cooling manifolds and N-1 supporting elements, each supporting element being arranged between two adjacent cooling manifolds.

Abstract: The invention relates to a concentric gas flow mixer in a multiple-flow turbomachine, comprising a nominally cylindrical upstream part and a downstream part having outer and inner lobes distributed peripherally around the tower of said mixer, characterised in that it comprises at least one modified lobe having a wall thickness, in at least one area, which is different from the other lobes, so as to modify the vibratory response of said mixer.

Abstract: The invention proposes a casing (30) of an aircraft turbine (16), intended to support a set of ring sectors (28) which partly delimits a channel for the passage of a gas stream through the turbine (16), where the casing (30) includes means for dynamic adjustment of the radial position of the ring sectors (28) by controlled injection of an air stream on to portions (36) of an annular wall (34) of the casing (30), where the casing (30) includes an upstream radial tab (38) which connects an upstream end of each ring sector (28), in the flow direction of the gas stream, to the casing (30), and a downstream radial tab (40) which connects a downstream end of each ring sector (28) to the casing (30), where both upstream and downstream radial tabs (38, 40) are made from a single piece with the casing (30), characterized in that each radial tab (38, 40) is made as two portions (42, 44) from different materials.

Abstract: The invention relates to a device (3) for attaching manifolds (1) for cooling the casing (2) of a preferably low-pressure turbine of a turbine engine by air jets, comprising a mounting (4) of said manifolds, shaped such as to keep said manifolds spaced apart from one another and a plurality of elements (5) for supporting said manifold mounting (4), each supporting element being attached to the casing, and connected to said manifold mounting (4) by connection means (6, 6?). Said device is characterised in that it comprises N cooling manifolds (1) and N?1 supporting elements (5), each supporting element (5) being arranged between two adjacent cooling manifolds.

Abstract: The present disclosure aims at achieving a mounting of a turbomachine stator blading while avoiding a delicate machining process of the engine casing. It also aims at simplifying the mounting as well as at reducing the costs, and at decreasing the number of item references for the engine. To achieve these objects, the turbomachine uses an extension of the engine casing. A turbomachine comprises at least one stator blading for air or gas stream flowing on the internal engine casing. The stator blading comprises a rim which is assembled on a radial extension of engine casing with an axial fastener. In a preferred embodiment of the turbomachine, the engine casing presents an annular wall provided with fingers originating axially from this wall and extending according to a curvature so that they present a radial extension tip against the rim of the stator blading.

Abstract: The invention proposes a casing (30) of an aircraft turbine (16), intended to support a set of ring sectors (28) which partly delimits a channel for the passage of a gas stream through the turbine (16), where the casing (30) includes means for dynamic adjustment of the radial position of the ring sectors (28) by controlled injection of an air stream on to portions (36) of an annular wall (34) of the casing (30), where the casing (30) includes an upstream radial tab (38) which connects an upstream end of each ring sector (28), in the flow direction of the gas stream, to the casing (30), and a downstream radial tab (40) which connects a downstream end of each ring sector (28) to the casing (30), where both upstream and downstream radial tabs (38, 40) are made from a single piece with the casing (30), characterised in that each radial tab (38, 40) is made as two portions (42, 44) from different materials.

Abstract: This blade attachment device comprises a shell (28) installed around an outer collar (23) of the pivot (15) of the blade (27) and capable of rotating by an angle sufficient for cleats (30, 31) to close the ends of the pivot groove and retain the root of the blade (27) in it, and mobile shims that cooperate to retain the root in the groove. Application to aircraft engines.

Abstract: A turbomachine blade including a plurality of blade sections stacked along a radial axis is disclosed. The projection of a line interconnecting the leading edges of the blade sections of the bottom stack onto a mid-plane presents a first longitudinal angle of inclination towards the leading edge that lies in the range 10° to 25°. The projection of a line interconnecting the leading edges of the blade sections of the intermediate stack presents a second longitudinal angle of inclination towards the trailing edge lying in the range 10° to 25°. The projection of a line interconnecting the leading edges of the blade sections of the top stack presents a third longitudinal angle of inclination towards the trailing edge lying in the range 20° to 50°. The bottom limit of the intermediate stack of the blade sections lies in the range 30% to 40% of the total radial height of the stack of blade sections.

Abstract: This blade attachment device comprises a shell (28) installed around an outer collar (23) of the pivot (15) of the blade (27) and capable of rotating by an angle sufficient for cleats (30, 31) to close the ends of the pivot groove and retain the root of the blade (27) in it, and mobile shims that cooperate to retain the root in the groove.

Abstract: The invention relates to a turbomachine blade comprising a plurality of blade sections stacked along a radial axis, and in which the projection of a line interconnecting the leading edges of the blade sections of the bottom stack onto a mid-plane presents a first longitudinal angle of inclination towards the leading edge that lies in the range 10° to 25°, the projection of a line interconnecting the leading edges of the blade sections of the intermediate stack presents a second longitudinal angle of inclination towards the trailing edge lying in the range 10° to 25°, the projection of a line interconnecting the leading edges of the blade sections of the top stack presents a third longitudinal angle of inclination towards the trailing edge lying in the range 20° to 50°, and the bottom limit of the intermediate stack of the blade sections lies in the range 30% to 40% of the total radial height of the stack of blade sections.

Abstract: A submarine system comprising a submarine device for operation within a fluid environment. The device is provided with a self-contained source of energy, propulsion components coupled to the energy source, maneuvering components and an environment observation device. A control station located remote from the submarine device is connected to it by means of a transmission cable, the cable being the sole means of transmitting command signals to the device and receiving observation results therefrom.