A heat exchanger for heat exchange between a first fluid and a second fluid has a plurality of tube sections, each comprising; an interior for passing the first fluid; an exterior for exposure to the second fluid; a first leg; a second leg; a turn joining the first leg to the second leg; and a first face and a second face. A support has at least one carbon member engaging the plurality of tube sections.

Renewable fuel power systems for vehicles, such as aircraft, are provided. For example, a system includes a storage tank, a reactor module, a heat exchanger unit, and a combustion engine. The storage tank is configured to store ammonia in liquid form. The reactor module is in fluid communication with the storage tank. The reactor module is configured to extract hydrogen from the ammonia, and output fuel which includes the extracted hydrogen. The heat exchanger unit is configured to heat the ammonia which flows from the storage tank to an input of the reactor module, using heat which is extracted from the fuel that is output from the reactor module. The combustion engine is configured to combust the fuel provided by the reactor module, to thereby produce mechanical power.

Renewable fuel power systems for vehicles, such as aircraft, are provided. For example, a system includes a storage tank, a reactor module, a heat exchanger unit, and a combustion engine. The storage tank is configured to store ammonia in liquid form. The reactor module is in fluid communication with the storage tank. The reactor module is configured to extract hydrogen from the ammonia, and output fuel which includes the extracted hydrogen. The heat exchanger unit is configured to heat the ammonia which flows from the storage tank to an input of the reactor module, using heat which is extracted from the fuel that is output from the reactor module. The combustion engine is configured to combust the fuel provided by the reactor module, to thereby produce mechanical power.

An oil distribution system uses an oil storage container to contain an air/oil separation unit, a heat exchanger, and an oil reservoir. The functions of oil storage, air/oil separation, and cooling are integrated in the container. Hot aerated oil enters the container at an air/oil separation unit. The air/oil separator deposits hot de-aerated oil into the oil reservoir. The oil reservoir transfers hot de-aerated oil to conduits in a heat exchanger. The heat exchanger uses fuel to cool the oil and warm the fuel. Cooled de-aerated oil is provided to a mechanical device for lubrication and warmed fuel is provided to power an engine. The container may alternatively receive hot aerated oil into the conduits in the heat exchanger. Cooled aerated oil is delivered to the air/oil separation unit to deposit cooled de-aerated oil into the reservoir. Cooled de-aerated oil is pumped to a mechanical device to provide lubrication.

The heat exchanger is generally ring-shaped and includes a plurality of heat exchange modules (2), which are mutually independent, being distributed about the axis (A1) of the ring. The modules (2) are assembled with one another, being successively spaced apart in pairs, a space (E1) being created between two adjacent modules (2). At least one of the spaces (E1) receives at least one conductive heat-transfer element (7) extending between respective walls of at least two adjacent the modules (2) which are oriented facing one another.

The heat exchanger is generally ring-shaped and includes a plurality of heat exchange modules (2), which are mutually independent, being distributed about the axis (A1) of the ring. The modules (2) are assembled with one another, being successively spaced apart in pairs, a space (E1) being created between two adjacent modules (2). At least one of the spaces (E1) receives at least one conductive heat-transfer element (7) extending between respective walls of at least two adjacent the modules (2) which are oriented facing one another.

Heat exchange devices for aircraft turbine engines include a heat exchanger and an inlet scoop comprising an air intake configured for supplying the heat exchanger. The air intake of the inlet scoop is divided into several mouthpieces, each defining an air flux supplying the heat exchanger.

A discharge duct (30) of an intermediate housing hub for an aircraft turbojet engine, comprises an inlet end (41) and an outlet end (42), intended to ensure the passage of air from at least one discharge inlet opening to at least one secondary outlet opening, and comprising an ejection grill (32) arranged at the outlet end (42), the ejection grill (32) comprising a plurality of fins (43), characterised in that the fins (43) comprise flow channels (44) for a fluid to be cooled, so as to form a heat exchange system.

A discharge duct (30) of an intermediate housing hub for an aircraft turbojet engine, comprises an inlet end (41) and an outlet end (42), intended to ensure the passage of air from at least one discharge inlet opening to at least one secondary outlet opening, and comprising an ejection grill (32) arranged at the outlet end (42), the ejection grill (32) comprising a plurality of fins (43), characterised in that the fins (43) comprise flow channels (44) for a fluid to be cooled, so as to form a heat exchange system.

An assembly is provided for a turbine engine. This assembly includes a primary duct, a bleed duct, a plurality of secondary ducts, a heat exchanger and a flow regulator. The bleed duct extends from a bleed duct inlet to a bleed duct outlet. The bleed duct inlet is fluidly coupled with the primary duct. The secondary ducts are arranged in parallel between the bleed duct outlet and the primary duct. The secondary ducts include a first duct and a second duct. The heat exchanger is configured with the second duct. The flow regulator is configured to direct at least a majority of fluid flowing through the bleed duct outlet to: (A) the first duct during a first mode of operation; and (B) the second duct during a second mode of operation.