Heat exchanger assemblies and cooling systems for evtol aircraft

A method for battery cooling, comprising:

• circulating, by a fluid conveyance assembly, a heat transfer fluid to a plurality of heat exchanger assemblies corresponding to a plurality of battery packs included in an electric aircraft, wherein each heat exchanger assembly comprises a first heat exchanger inlet-outlet and a second heat exchanger inlet-outlet configured to receive or discharge the heat transfer fluid, and a heat exchanger plate;
• and
• providing a turbulating flow of the heat transfer fluid through cooling channels of the heat exchanger plate by a plurality of dimples, wherein the plurality of dimples in the cooling channels are arranged in a staggered manner such that adjacent dimples in a flow direction of the cooling channels are extended from opposite sides of the cooling channel;
• wherein operations of circulating the heat transfer fluid comprise;
• in a first operating period, receiving the heat transfer fluid from the first heat exchanger inlet-outlet and discharging the heat transfer fluid to the second heat exchanger inlet-outlet;
• and
• in a second operating period, receiving the heat transfer fluid from the second heat exchanger inlet-outlet and discharging the heat transfer fluid to the first heat exchanger inlet-outlet.

A power supply system for an aircraft, comprising:

• a plurality of battery packs configured to be installed within a wing portion of the aircraft, wherein each battery pack is configured to be connected to an electric engine of the aircraft to provide power;
• a plurality of heat exchanger assemblies corresponding to the plurality of battery packs of the aircraft, each heat exchanger assembly comprising a first heat exchanger inlet-outlet and a second heat exchanger inlet-outlet configured to receive a heat transfer fluid or discharge the heat transfer fluid;
• and
• a fluid conveyance assembly coupled to the heat exchanger assemblies and comprising a first main inlet-outlet and a second main inlet-outlet, and configured to circulate the heat transfer fluid in parallel to the heat exchanger assemblies, the first main inlet-outlet and a second main inlet-outlet being arranged at a same location of the aircraft, the fluid conveyance assembly further comprising:
• a plurality of conduit segments configured to passively balance the heat transfer fluid flowing into each of the heat exchanger assemblies,
• wherein each heat exchanger assembly comprises a heat exchanger plate configured to receive the heat transfer fluid from the first heat exchanger inlet-outlet and discharge the heat transfer fluid to the second heat exchanger inlet-outlet in a first operating period, and to receive the heat transfer fluid from the second heat exchanger inlet-outlet and discharge the heat transfer fluid to the first heat exchanger inlet-outlet in a second operating period before or after the first operating period.

A power supply system for an aircraft, comprising:

• a plurality of battery packs configured to be installed within a wing portion of the aircraft, wherein each battery pack is configured to be connected to an electric engine of the aircraft to provide power;
• a plurality of heat exchanger assemblies respectively connected to battery pack enclosures of the plurality of battery packs, each heat exchanger assembly comprising a cooling channel;
• and
• a fluid conveyance assembly coupled to the plurality of heat exchanger assemblies and configured to circulate a heat transfer fluid through the cooling channels in the heat exchanger assemblies;
• wherein each cooling channel comprises a plurality of dimples arranged in a staggered manner such that adjacent dimples in a flow direction of the cooling channels are extended from opposite sides of the cooling channels;
• and
• wherein the adjacent dimples in the flow direction are partially indented from laterally opposite sides of top or bottom surfaces of the cooling channels such that a first height of the cooling channels in a region not having a dimple is greater than a second height of the cooling channels in a region having a dimple.