Abstract: An annular heat exchanger for a turbomachine, is intended, for example, to be supported by an annular ferrule of a housing of the turbomachine, and includes an annular one-piece part having a first fluid circuit having at least one first conduit and at least one second conduit extending in an annular manner. The first conduit and the second conduit lead into a first cavity formed on a first circumferential end of said annular part, and the heat exchanger includes detachable sealing means which are applied to said first end and designed to allow a flow of fluid from the second conduit into the first cavity then into the first conduit.

Abstract: The invention relates to an annular assembly for a dual-flow turbomachine having a longitudinal axis (A) and comprising a casing (12) with an annular shell (14), one face of which supports a piece of annular equipment, a plurality of means of attachment (18) for attaching the equipment to the annular shell (14) being distributed around the longitudinal axis (A) and allowing the equipment (16) a degree of freedom in the tangential direction relative to the annular shell (14), characterised in that each means of attachment (18) comprises a rail (20) integral with the annular equipment (16) and arranged radially between a first radially internal plate (22) and a second, radially external plate (24) and capable of sliding in the tangential direction between the first plate (22) and the second plate (24), and in that a removable support element (56) is securely connected to the annular shell and to the first plate (22) and second plate (24).

Abstract: A pressure valve including a body including at least one admission opening and at least one discharge opening, a slide valve sliding in the body, the slide valve defining a chamber, with the body, and including a head arranged facing a seat of the admission opening, a spring pressing the head of the slide valve against the seat, a lip for applying the head to the seat. The head includes at least one hole bringing the chamber into communication with the discharge opening, each hole being arranged facing the seat and downstream from the lip in relation to the admission opening in order to reduce the pressure in the chamber by a Venturi effect when the slide valve is open.

Abstract: A method for manufacturing an annular heat exchanger intended to be mounted on the radially inner or outer face of an annular shell of a casing of a double-flow turbomachine, the method including: obtaining by extrusion a heat exchanger preform by a die shaped so that the preform includes: first pipes for the circulation of a fluid to be cooled, second pipes arranged on either side of the first pipes in a direction perpendicular to the direction of extrusion; making a hole from the outside in the preform, the hole leading into one of the second pipes of the preform; and introducing into the hole of the second given pipe a member for partially closing off its passage cross-section.

Abstract: An annular heat exchanger with a longitudinal axis for a turbomachine, intended for example to be supported by an annular shell of a casing of the turbomachine, includes a one-piece annular part having a first fluidic circuit having at least one first conduit and at least one second conduit extending annularly and a second fluidic circuit having at least one first conduit and at least one second conduit extending annularly and arranged in a direction perpendicular to the longitudinal direction on either side of the first conduit and second conduit of the first circuit.

Abstract: The invention relates to a device for monitoring the lifetime of at least one hydraulic apparatus of an aircraft that is subject to ventilations in hydraulic pressure during flight, comprising an interface for receiving measurement data which are representative of hydraulic pressure (P).

Abstract: The invention relates to a device for monitoring the lifetime of at least one hydraulic apparatus of an aircraft that is subject to ventilations in hydraulic pressure during flight, comprising an interface for receiving measurement data which are representative of hydraulic pressure (P).

Abstract: The invention relates to an annular assembly for a dual-flow turbomachine having a longitudinal axis (A) and comprising a casing (12) with an annular shell (14), one face of which supports a piece of annular equipment, a plurality of means of attachment (18) for attaching the equipment to the annular shell (14) being distributed around the longitudinal axis (A) and allowing the equipment (16) a degree of freedom in the tangential direction relative to the annular shell (14), characterised in that each means of attachment (18) comprises a rail (20) integral with the annular equipment (16) and arranged radially between a first radially internal plate (22) and a second, radially external plate (24) and capable of sliding in the tangential direction between the first plate (22) and the second plate (24), and in that a removable support element (56) is securely connected to the annular shell and to the first plate (22) and second plate (24).

Abstract: A heat exchange and noise reduction panel the panel for an aircraft comprising: an external surface intended to be swept by an airflow and from which fins extend along a first and a second main predetermined direction; cavities forming Helmholtz resonators, linked to the first ends of channels for the passage of air, the second ends of which communicate with said airflow, such that said channels form necks, referred to as Helmholtz resonators, extending substantially along the first direction; and at least one oil flow chamber extending between said external surface and said at least one cavity, and intended to discharge the thermal energy carried by the oil, wherein said channels are formed, at least in part, inside said fins.

Abstract: An annular heat exchanger for a turbomachine, is intended, for example, to be supported by an annular ferrule of a housing of the turbomachine, and includes an annular one-piece part having a first fluid circuit having at least one first conduit and at least one second conduit extending in an annular manner. The first conduit and the second conduit lead into a first cavity formed on a first circumferential end of said annular part, and the heat exchanger includes detachable sealing means which are applied to said first end and designed to allow a flow of fluid from the second conduit into the first cavity then into the first conduit.

Abstract: An annular heat exchanger with a longitudinal axis for a turbomachine, intended for example to be supported by an annular shell of a casing of the turbomachine, includes a one-piece annular part having a first fluidic circuit having at least one first conduit and at least one second conduit extending annularly and a second fluidic circuit having at least one first conduit and at least one second conduit extending annularly and arranged in a direction perpendicular to the longitudinal direction on either side of the first conduit and second conduit of the first circuit.

Abstract: A method for manufacturing an annular heat exchanger intended to be mounted on the radially inner or outer face of an annular shell of a casing of a double-flow turbomachine, the method including: obtaining by extrusion a heat exchanger preform by a die shaped so that the preform includes: first pipes for the circulation of a fluid to be cooled, second pipes arranged on either side of the first pipes in a direction perpendicular to the direction of extrusion; making a hole from the outside in the preform, the hole leading into one of the second pipes of the preform; and introducing into the hole of the second given pipe a member for partially closing off its passage cross-section.

Abstract: An assembly for a turbine engine having an oil circuit. The oil circuit includes an air/oil heat exchanger, a primary bypass pipe connecting an intake of the air/oil heat exchanger to an outlet of the air/oil heat exchanger and surrounding the air/oil heat exchanger so as to exchange heat with the air/oil heat exchanger. The oil circuit further includes and a secondary bypass pipe of the primary pipe connecting the upstream end of the primary bypass pipe to the downstream end of the primary bypass pipe. The oil circuit also includes at least one valve for controlling the passage of the flow of oil into the primary and secondary bypass pipes and means for controlling the opening of said at least one valve for a temperature lower than a threshold temperature.

Abstract: A pressure valve including a body including at least one admission opening and at least one discharge opening, a slide valve sliding in the body, the slide valve defining a chamber, with the body, and including a head arranged facing a seat of the admission opening, a spring pressing the head of the slide valve against the seat, a lip for applying the head to the seat. The head includes at least one hole bringing the chamber into communication with the discharge opening, each hole being arranged facing the seat and downstream from the lip in relation to the admission opening in order to reduce the pressure in the chamber by a Venturi effect when the slide valve is open.

Abstract: An assembly for a turbine engine having an oil circuit. The oil circuit includes an air/oil heat exchanger, a primary bypass pipe connecting an intake of the air/oil heat exchanger to an outlet of the air/oil heat exchanger and surrounding the air/oil heat exchanger so as to exchange heat with the air/oil heat exchanger. The oil circuit further includes and a secondary bypass pipe of the primary pipe connecting the upstream end of the primary bypass pipe to the downstream end of the primary bypass pipe. The oil circuit also includes at least one valve for controlling the passage of the flow of oil into the primary and secondary bypass pipes and means for controlling the opening of said at least one valve for a temperature lower than a threshold temperature.

Abstract: A heat exchange and noise reduction panel the panel for an aircraft comprising: an external surface intended to be swept by an airflow and from which fins extend along a first and a second main predetermined direction; cavities forming Helmholtz resonators, linked to the first ends of channels for the passage of air, the second ends of which communicate with said airflow, such that said channels form necks, referred to as Helmholtz resonators, extending substantially along the first direction; and at least one oil flow chamber extending between said external surface and said at least one cavity, and intended to discharge the thermal energy carried by the oil, characterized in that wherein said channels are formed, at least in part, inside said fins.