A heat exchange system for a turbomachine includes a heat exchanger that has a support wall extending along a longitudinal direction L and a plurality of fins each extending along a radial direction from a radially external surface of the support wall. The heat exchanger further includes a first profiled wall arranged upstream from the fins and configured to guide and slow down the flow of air entering the heat exchanger through the fins. A second profiled wall is arranged downstream from the fins and configured to accelerate the flow of air leaving the heat exchanger. Each first and second profiled wall is attached to the support wall via support elements extending radially from the radially external surface.

Described is a cooler having: a heat exchanger for dissipating heat from a medium, for example oil, a fan having a fan housing, a fan wheel and a motor, a control unit for controlling the motor, a sensor unit for detecting an operating parameter of the heat exchanger and/or of the fan, the sensor unit being connected to the control unit in order to set an operating state of the cooler, the fan housing having a recess in which the control unit is arranged together with the sensor unit.

An assembly includes a valve integration unit attached to a transmission oil heater. The valve integration unit includes a valve mechanism and a housing having first to sixth fluid ports for oil input and output. The interior space of the housing has a valve chamber to receive a thermal valve mechanism has a temperature responsive actuator. A bypass flow passage is located outside the heat exchanger and is in fluid communication with oil inlet and outlet manifolds through first and second bypass holes provided in the heat exchanger.

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.

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.

A tank for a heat exchanger includes an extruded tank section having a generally constant extrusion profile extending in a longitudinal direction from a first tank end to a second tank end. A first planar end cap is joined to the extruded tank section near the first tank end, and a second planar end cap is joined to the extruded tank section near the second tank end. Together, the extruded tank section and first and second end caps can at least partially define an internal tank volume. The first and second planar end caps are both arranged at non-perpendicular angles to the longitudinal direction.

An exchanger system comprising two heat exchangers, a bypass line which extends between an inlet and an outlet, a line connected between the bypass line and a first orifice of each heat exchanger, a return line connected to two second orifices of the two heat exchangers and to the bypass line, three valves, and a controller which commands each valve alternately to open or to close. With such an arrangement, the intensities of the pressure peaks due to plugs are limited by distribution of the flow of the heat-transfer fluid in two parallel lines.

A heat exchanger for a transmission unit of an aircraft is described that comprises: a first module defining a first feed path for a first fluid to be cooled; a second module defining a second feed path for a second cooling fluid; the first and second feed paths being thermally coupled to each other; each second module comprising: at least one cell formed by an inlet for a second cooling fluid; an outlet for the second cooling fluid, which is arrange on the opposite side to the inlet along a first direction; a first wall thermally coupled to the first path; a pair of second walls; and a plurality of fins projecting in a cantilever fashion from the first wall. The heat exchanger further comprises at least a first row of fins, which lie on a plane orthogonal to the first direction, the fins of the first row extending at progressively increasing distances from one of the second walls along a second direction orthogonal to the first direction.

The invention relates to a guide vane intended to be arranged in all or part of an air flow of an aircraft bypass turbomachine fan, the vane comprising an aerodynamic part equipped with at least one interior lubricant cooling passage delimited in part by an intrados wall and an extrados wall of the vane, there being flow-disturbing lugs, made as one piece with one of the intrados and extrados walls, passing across the passage. According to the invention, in any plane of section passing orthogonally through the lugs, the space defined between these lugs has a geometry defined exclusively by a set of annulus shapes of the same dimensions, partially overlapping one another and each in part delimiting at least two of these lugs.

A heat exchanger of a gas turbine engine includes a casing having a stepped incident-flow profile. An air volume flow is, in the region of the incident-flow profile, diverted such that a recirculation zone with a separation bubble forms in the flow. Downstream of the incident-flow profile, is a further stepped incident-flow profile. The flow is diverted such that, downstream of the further incident-flow profile, a further recirculation zone forms in which a separation bubble is present. In the region of the incident-flow profile and/or the further incident-flow profile, is an inlet of a flow duct which runs in the casing in the direction of a mouth. An air volume flow conducted through the flow duct emerges from the mouth at such an angle relative to the flow direction of the air volume flow that, downstream of the mouth, a recirculation zone with a separation bubble forms.