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.

A cooling apparatus for a hydrostatic transmission includes a cooling body to be coupled with a hydrostatic transmission, a sidewall member protruding from the cooling body to surround a cooling flow path which cools a working fluid supplied from the hydrostatic transmission and discharges the working fluid into the hydrostatic transmission or a storage tank, an installing member protruding from the cooling body at a position spaced apart from the sidewall member to be disposed inside the sidewall member, a detour member connected to the installing member and protruding from the cooling body to extend in a first axial direction to allow the working fluid, which flows along the cooling flow path, to make a detour, and a plurality of protruding members protruding from the cooling body to be spaced apart from each of the sidewall member, the installing member, and the detour member in the cooling flow path.

A heat exchanger designed to be fixed to a turbomachine wall delimiting a gas flow stream, this exchanger including a body with a front face through which the gas flow passes; an attachment face to the wall; an external face opposite the attachment face and connected to the front face; two lateral faces connected to the front face; a cover surrounding the front face and extending along the prolongation of the external face and the lateral faces, to delimit an intake with an area smaller than the area of the front face, this intake being located upstream from the front face relative to the gas flow stream.

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 hydraulic unit includesa hydraulic pump, a motor configured to drive the hydraulic pump, an oil cooler configured to cool hydraulic oil discharged from the hydraulic pump, a cooling fan configured to supply cooling air to the motor and the oil cooler, a shroud provided between the cooling fan and the oil cooler, arid a controller disposed adjacent to the motor. The controller controls the motor. The oil cooler includes a pair of headers, and a heat exchange unit provided between the pair of headers. The shroud includes a wall section covering at least one of the pair of headers. The controller includes a drive circuit configured to drive the motor, and a heat sink that cools the drive circuit. Part of the cooling air blown out from the cooling fan is guided toward the heat sink.

A guide vane for a twin-spool aircraft turbomachine has an aerodynamic part that includes an internal lubricant cooling passage extending along a principal lubricant flow direction. The aerodynamic part is made in a single piece and also includes heat transfer fins arranged in the passage connecting the intrados and extrados walls and extending approximately parallel to the direction, these fins being distributed in successive rows along the principal direction and made such that for two rows of staggered directly consecutive fins, a first row includes fins forming a positive acute angle A1 with a dummy reference plane, while a second row includes fins forming a negative acute angle A2 with this plane.

A heat exchanger system includes a core structure with an oil flow path configured to receive an oil flow. The heat exchanger system also includes a fuel flow path included in the core structure and configured to receive a fuel flow. The fuel flow path is coupled to the oil flow path to allow the fuel flow to receive heat from the oil flow in the oil flow path. Also, the heat exchanger system includes a supplemental airflow path defined at least partly by the core structure and configured to receive a supplemental airflow that receives heat from at least one of the oil flow and the fuel flow.

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.

An oil cooler includes flat tubes layered together with a clearance, wherein cooling water flows through the clearance. Each flat tube includes a first plate, a second plate, and a fin plate held between the first plate and the second plate. The first plate is recessed to form a fin plate accommodation portion accommodating the fin plate, wherein a thin portion is formed outside of the fin plate accommodation portion in a longitudinal direction of the flat tube. An oil port is provided at the thin portion. Each flat tube includes a guide wall at a lateral periphery thereof, wherein the guide wall faces the oil port in a width direction, and projects in a layering direction. The guide wall, the thin portion, and a lateral wall of the oil port form a nozzle portion to guide cooling water in the longitudinal direction.

A cooling apparatus for a hydrostatic transmission includes a cooling body to be coupled with a hydrostatic transmission, a sidewall member protruding from the cooling body to surround a cooling flow path which cools a working fluid supplied from the hydrostatic transmission and discharges the working fluid into the hydrostatic transmission or a storage tank, an installing member protruding from the cooling body at a position spaced apart from the sidewall member to be disposed inside the sidewall member, a detour member connected to the installing member and protruding from the cooling body to extend in a first axial direction to allow the working fluid, which flows along the cooling flow path, to make a detour, and a plurality of protruding members protruding from the cooling body to be spaced apart from each of the sidewall member, the installing member, and the detour member in the cooling flow path.