The invention relates to a guide vane for a twin-spool aircraft turbomachine, of which the aerodynamic part (32) comprises an internal lubricant cooling passage (50a) extending along a principal lubricant flow direction (52a).

According to the invention, the aerodynamic part is made in a single piece and also comprises heat transfer fins (80a, 80b) arranged in the passage (50a) connecting the intrados and extrados walls (70, 72) and extending approximately parallel to the direction (52a), these fins being distributed in successive rows along the principal direction (52a) and made such that for two rows (R1, R2) of staggered directly consecutive fins, the row (R1) comprises fins (80a) forming a positive acute angle A1 with a dummy reference plane (Pf), while the row (R2) comprises fins (80b) forming a negative acute angle A2 with this plane (Pf).

A three-stream engine is provided. The three-stream engine includes a fan section, a core engine disposed downstream of the fan section, and a core cowl annularly encasing the core engine and at least partially defining a core duct. A fan cowl is disposed radially outward from the core cowl and annularly encasing at least a portion of the core cowl. The fan cowl at least partially defining an inlet duct and a fan duct. The fan duct and the core duct at least partially co-extending axially on opposite sides of the core cowl. A heat exchanger disposed within the fan duct. The heat exchanger provides for thermal communication between a fluid flowing through fan duct and a motive fluid flowing through the heat exchanger.

A heat exchanger is provided including an inlet manifold and an outlet manifold arranged generally parallel to the inlet manifold and being spaced therefrom by a distance. A plurality of rows of microtubes is aligned in a substantially parallel relationship. The plurality of rows of microtubes is configured to fluidly couple the inlet manifold and the outlet manifold. Each of the plurality of rows includes a plurality of microtubes.

An energy store of a motor vehicle may include at least one battery cell and a fluid channel having a temperature control fluid that may control a temperature of the at least one battery cell. The fluid channel may be defined by a fluid channel arrangement having two walls and a plurality of spacers arranged therebetween. The plurality of spacers may be configured for a needs-based temperature control of the at least one battery cell. The plurality of spacers may be arranged so that a coolant flow is conducted directly to a hot spot of the at least one battery cell. At least one of the two walls may comprise an organic sheet and may be connected, via glue or welding, to the plurality of spacers.

A heat exchanger comprises a conduit defining an inlet flow path for a fluid; a heat exchanger matrix disposed to receive a flow from the inlet flow path; and a swirler disposed within the conduit and arranged to improve dispersion of a flow from the inlet flow path over the heat exchanger matrix.

A bonded dissimilar material heat transfer assembly is provided. The assembly comprises a frame component, a thin stamped component and at least one dissimilar metal component having means for heat transfer and having a higher thermal conductivity than the frame component and stamped component. The heat transfer assembly includes a novel geometry such that distortion caused by mismatch of thermal expansion rates does not affect the normally planar shape of the assembly. Such a construction leads to higher thermal performance, lighter weight, less cost, and higher reliability than similar prior art heat exchanger assemblies.

A heat sink with shape-optimized fins provides for improved heat transfer. Synthetic jets create vortices which enhance heat transfer and cooling of downstream fins, while the shape of the fins limits pressure drop in the flow over the cooling fins.

The invention relates to a guide vane (24) for a dual flow aircraft turbine engine, the aerodynamic part (32) of the vane comprising an inner duct (50a) for lubricant cooling extending in a main direction (52a) and being partly bounded by a pressure side wall (70) and a suction side wall (72) of the vane.

According to the invention, the aerodynamic part (32) of the vane is embodied from as a single piece, including also the heat transfer fins (80), arranged in the duct (50a) expanding substantially parallel to the direction (52a), the fins (80) being spaced from each other depending on the direction (52a) as well as a transversal direction (60) of the vane, so that at least some of the fins (80) are arranged substantially staggered.

A pin for a heat exchanger. The pin includes: a monolithic top section; a monolithic bottom section; and a middle section comprising a plurality of spaced apart sub-pins extending between the top section and the bottom section, wherein the plurality of sub-pins define one or more windows for allowing fluid flow through the middle section. Also disclosed is a layer of a heat exchanger including the pin, as well as a heat exchanger including the layer, and a method of making a layer for a heat exchanger.

A cooling jacket (14) for cooling an electric motor, in particular a stator (23), wherein a first spiral line (16) for transporting a coolant is formed at least partially on the cooling jacket (14). The aim of the invention is to provide a cooling system that is optimized in terms of mounting space and ensures axially equalized cooling. This aim is achieved in that a second spiral line (17) for transporting coolant is formed at least partially, and in that based on a common spiral axis R, both spiral lines (16, 17) form an axially integrated double spiral, wherein the first spiral line (16) is an inflow line and the second spiral line (17) is a return flow line. The invention further relates to a deflection unit (12) for the return into the second line (17), which substantially prevents the static pressure from dropping.