Abstract: A surface heat exchanger for an aircraft turbomachine includes a support wall, a panel parallel to the support wall, partitions connecting the wall to the panel to define channels in which an air flow flows, and fins situated in the channels. The panel has a central part parallel to the wall and a downstream part that is inclined with respect to the wall. An upstream end is connected to the central part and a downstream end is situated at a distance from the wall and delimits with the latter a main outlet of the channels. The downstream part has fixed flaps disposed one after another so as to delimit between one another additional outlets of the channels.

Abstract: A plate heat exchanger, in particular for an aircraft turbo machine, between a first fluid and a second fluid, the first fluid being intended to circulate in a first direction and the second fluid being intended to circulate in a second direction different from the first direction, the heat exchanger having stacked stages for circulation of the first fluid, and profiled elements at the inlet and outlet of the stages, the profiled elements having a sawtooth-shaped cross-section and defining channels converging at the inlet of the stages and diverging at the outlet of the stages.

Abstract: A heat exchange system of a turbomachine, includes a heat exchanger including a support wall, a plurality of fins each extending in a radial direction from a radially outer surface of the support wall, and a cover covering the fins, wherein the cover is connected, upstream in the direction of flow of the air flow, to a first profiled wall, and downstream to a second profiled wall, the first profiled wall being arranged upstream from the fins and configured to guide and slow down the flow of air entering the heat exchanger through the fins, and the second profiled wall being arranged downstream from the fins and configured so as to accelerate the flow of air leaving the heat exchanger, wherein the cover has an at least partially curvilinear aerodynamic profile and an outer peripheral surface having surface continuity with radially outer surfaces of the first and second walls.

Abstract: A counter-current heat exchanger for a turbomachine comprising a first and a second circuit, the first and the second circuit being respectively configured to receive a first gas flow and a second gas flow, each circuit including a secondary inlet manifold, an exchanging part and a secondary outlet manifold; the exchanging parts of the first circuit and of the second circuit being delimited by exchange walls configured to direct the first and the second gas flow along a first direction; and wherein the secondary inlet manifold and the secondary outlet manifold of the first circuit extend along a second direction substantially perpendicular to the first direction, and open onto a same face of the exchanger.

Abstract: The invention relates to a heat exchanger comprising a support wall and a first plurality of fins that each stand proud from an outer surface of the support wall and are designed to have a first air flow pass over them. According to the invention, the heat exchanger comprises, downstream of the first plurality of fins, a second plurality of fins that each stand proud from the outer surface of the support wall, the first and second pluralities of fins being separated by distribution means which are configured in such a way that the first air flow flows outside the second plurality of fins and a second air flow flowing outside the first plurality of fins passes through the second plurality of fins.

Abstract: 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.

Abstract: 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.

Abstract: A heat exchange system of a turbomachine, includes a heat exchanger including a support wall, a plurality of fins each extending in a radial direction from a radially outer surface of the support wall, and a cover covering the fins, wherein the cover is connected, upstream in the direction of flow of the air flow, to a first profiled wall, and downstream to a second profiled wall, the first profiled wall being arranged upstream from the fins and configured to guide and slow down the flow of air entering the heat exchanger through the fins, and the second profiled wall being arranged downstream from the fins and configured so as to accelerate the flow of air leaving the heat exchanger, wherein the cover has an at least partially curvilinear aerodynamic profile and an outer peripheral surface having surface continuity with radially outer surfaces of the first and second walls.

Abstract: Exchanger (1) of heat between a first fluid flowing in a longitudinal direction (X) and a second fluid, the said exchanger (1) comprising: two parallel plates (6) distant from one another; at least a first and second row (8a, 8b) of fins (9) arranged perpendicularly between the said plates (6), each fin (9) being delimited longitudinally by a first edge (10) and a second edge (11), the said first edge (10) comprising at each of its ends a region of connection with the corresponding plate (6); characterised in that the said connection regions of the said first edge (10) are respectively inclined with respect to a normal to the plates (6) in a plane (P) perpendicular to the said plates (6) and parallel with the direction (X), the said first edge (10) and the said second edge (11) of each of the fins (9) having identical profiles in the said plane (P).