Abstract: An exemplary cooling system includes a heat transfer device having a base and a plurality of curved fins defining a curved air flow channel. Air flow is provided through the air flow channel, and a plurality of openings through a fin communicate air flow from a first side to a second side of the curved fin.

Abstract: An exemplary cooling system includes a heat transfer device having a base and a plurality of curved fins defining a curved air flow channel. Air flow is provided through the air flow channel, and a plurality of openings through a fin communicate air flow from a first side to a second side of the curved fin.

Abstract: An exemplary cooling system includes a heat transfer device having a base and a plurality of curved fins defining a curved air flow channel. Air flow is provided through the air flow channel, and a plurality of openings through a fin communicate air flow from a first side to a second side of the curved fin.

Abstract: A heat exchanger includes a plurality of channels and one or more active flow disruption members disposed at an entrance to the plurality of channels. The active flow disruption members are configured to induce unsteadiness in a flow through the plurality of channels to increase thermal energy transfer in the plurality of channels. A method for transferring thermal energy from a heat exchanger includes locating one or more active flow disruption members at an entrance to a plurality of channels of the heat exchanger. A flow is directed across the one or more active flow disruption members into the plurality of channels and an unsteadiness is produced in the flow via the one or more active flow disruption members. The unsteadiness in the flow increases the transfer of thermal energy between the heat exchanger and the flow.

Abstract: A pressure monitoring system for a fuel tank includes a supply line fluidly coupling a fluid source with at least one fuel tank for supplying an inert gas to the at least one fuel tank. Also included is a pressure relief valve in communication with the supply line configured to detect a pressure differential between a supply line pressure and an ambient pressure. Further included is a pressure sensor configured to detect the supply line pressure. Yet further included is a controller in operable communication with the pressure sensor and the fluid source, wherein the controller is configured to modify a flow rate of the inert gas in the supply line upon detection of the supply line pressure exceeding a predetermined pressure limit.

Abstract: A thermoelectric device (100, 220) includes a plurality of conductor portions (120-124) including a first angled side portion (134) and a second angled side portion (135). The thermoelectric device (100, 220) also includes a plurality of conductor members (170-174) including a first angled side section (181) and a second angled side section (182). A plurality of P-type thermoelectric members (210-213) interconnect corresponding ones of the first angled side portions (134) with the first angled side sections (181). A plurality of N-type thermoelectric members (200-204) interconnect corresponding ones of the second angled side portions (135) with the second angled side sections (182). Electric flow through the plurality of conductor portions (120-124) and the plurality of conductor members (170-174) passes along a first predefined curvilinear path and a heat flux passes along a second predefined curvilinear path.

Abstract: According to one aspect of the invention, an electronics package includes an enclosure and one or more thermal energy generating components disposed in the enclosure. A radial heat sink is disposed in the enclosure including a blower disposed in the radial heat sink and a plurality of fins extending from a periphery of the blower toward a perimeter of the radial heat sink. The plurality of fins define a plurality of channels having a plurality of channel exits at the perimeter of the radial heat sink. The radial heat sink configured to dissipate thermal energy from the one or more components which are arranged around the heat sink according to heat flux requirements of each component. An air inlet extends through the enclosure and is connected to the blower to direct air to the blower in a direction substantially perpendicular to the first longitudinal face and/or the second longitudinal face.

Abstract: A cooling system includes a compressor for compressing a refrigerant from a subcritical state to a supercritical state, a cooler for transferring heat from the refrigerant, an expander for expanding the refrigerant in the supercritical state, an expansion valve for expanding the refrigerant from the supercritical state to the subcritical state and an evaporator for transferring heat from a cooling fluid to the refrigerant in the subcritical state. Work extracted by the expander provides power to the compressor. A method for cooling a vehicle includes compressing a refrigerant from a subcritical state to a supercritical state, cooling the refrigerant, expanding the refrigerant in the supercritical state where work produced by expanding the refrigerant is used to compress the refrigerant, expanding the refrigerant from the supercritical state to the subcritical state, cooling a cooling fluid with the refrigerant in the subcritical state and cooling vehicle components with the cooling fluid.

Abstract: A heat sink includes a blower located in the heat sink and a plurality of fins extending from a periphery of the blower toward a perimeter of the heat sink. The plurality of fins define a plurality of channels each having a channel inlet located at the blower and a channel exit located at the perimeter of the heat sink. The plurality of channels vary in length around the perimeter of the heat sink A velocity of an air flow from the blower at each channel inlet is substantially equal for each channel of the plurality of channels, and a total pressure drop from the channel inlet to the channel exit is substantially equal for each channel of the plurality of channels.

Abstract: An aircraft power distribution architecture including an Auxiliary Power Unit, a power distributor, and an electric generator distributes power to multiple aircraft systems.

Abstract: A heat exchanger includes one or more passages and one or more metal foam sections adjacent the passage to promote an exchange of heat relative to the passage. The metal foam section includes a nominal thermal conductivity gradient there though to provide a desirable balance of heat exchange properties within the metal foam section.

Abstract: According to one aspect of the invention, an electronics package includes an enclosure and one or more thermal energy generating components disposed in the enclosure. A radial heat sink is disposed in the enclosure including a blower disposed in the radial heat sink and a plurality of fins extending from a periphery of the blower toward a perimeter of the radial heat sink. The plurality of fins define a plurality of channels having a plurality of channel exits at the perimeter of the radial heat sink. The radial heat sink configured to dissipate thermal energy from the one or more components which are arranged around the heat sink according to heat flux requirements of each component. An air inlet extends through the enclosure and is connected to the blower to direct air to the blower in a direction substantially perpendicular to the first longitudinal face and/or the second longitudinal face.

Abstract: A heat sink includes a blower located in the heat sink and a plurality of fins extending from a periphery of the blower toward a perimeter of the heat sink. The plurality of fins define a plurality of channels each having a channel inlet located at the blower and a channel exit located at the perimeter of the heat sink. The plurality of channels vary in length around the perimeter of the heat sink A velocity of an air flow from the blower at each channel inlet is substantially equal for each channel of the plurality of channels, and a total pressure drop from the channel inlet to the channel exit is substantially equal for each channel of the plurality of channels.

Abstract: A heat exchanger includes a plurality of channels and one or more active flow disruption members disposed at an entrance to the plurality of channels. The active flow disruption members are configured to induce unsteadiness in a flow through the plurality of channels to increase thermal energy transfer in the plurality of channels. A method for transferring thermal energy from a heat exchanger includes locating one or more active flow disruption members at an entrance to a plurality of channels of the heat exchanger. A flow is directed across the one or more active flow disruption members into the plurality of channels and an unsteadiness is produced in the flow via the one or more active flow disruption members. The unsteadiness in the flow increases the transfer of thermal energy between the heat exchanger and the flow.

Abstract: An exemplary cooling system includes a heat transfer device having a base and a plurality of curved fins defining a curved air flow channel. Air flow is provided through the air flow channel, and a plurality of openings through a fin communicate air flow from a first side to a second side of the curved fin.

Abstract: A thermoelectric device (100, 220) includes a plurality of conductor portions (120-124) including a first angled side portion (134) and a second angled side portion (135). The thermoelectric device (100, 220) also includes a plurality of conductor members (170-174) including a first angled side section (181) and a second angled side section (182). A plurality of P-type thermoelectric members (210-213) interconnect corresponding ones of the first angled side portions (134) with the first angled side sections (181). A plurality of N-type thermoelectric members (200-204) interconnect corresponding ones of the second angled side portions (135) with the second angled side sections (182). Electric flow through the plurality of conductor portions (120-124) and the plurality of conductor members (170-174) passes along a first predefined curvilinear path and a heat flux passes along a second predefined curvilinear path.

Abstract: A cooling system includes a compressor for compressing a refrigerant from a subcritical state to a supercritical state, a cooler for transferring heat from the refrigerant, an expander for expanding the refrigerant in the supercritical state, an expansion valve for expanding the refrigerant from the supercritical state to the subcritical state and an evaporator for transferring heat from a cooling fluid to the refrigerant in the subcritical state. Work extracted by the expander provides power to the compressor. A method for cooling a vehicle includes compressing a refrigerant from a subcritical state to a supercritical state, cooling the refrigerant, expanding the refrigerant in the supercritical state where work produced by expanding the refrigerant is used to compress the refrigerant, expanding the refrigerant from the supercritical state to the subcritical state, cooling a cooling fluid with the refrigerant in the subcritical state and cooling vehicle components with the cooling fluid.

Abstract: An avionics cooling system includes a first heat exchange system, a second heat exchange system and a vapor cycle system. The second heat exchange system has a heat sink capacity that is generally out of phase with a heat sink capacity of the first heat exchange system. The vapor cycle includes a fluid loop in communication with the first and second heat exchange systems and the fluid loop transfers heat to the first and second heat exchange systems. A method for cooling aircraft components includes selectively directing a fluid having an elevated temperature in a fluid loop of a vapor cycle system to a first heat exchanger to transfer heat from the fluid to a fuel based on a heat sink capacity of the fuel, selectively directing the fluid to a second heat exchanger to transfer heat from the fluid to air based on a heat sink capacity of the air, and cooling aircraft components with the fluid.

Abstract: A heat exchanger includes one or more passages and one or more metal foam sections adjacent the passage to promote an exchange of heat relative to the passage. The metal foam section includes a nominal thermal conductivity gradient there though to provide a desirable balance of heat exchange properties within the metal foam section.

Abstract: An air-cooled heat exchange device for cooling an object such as an electronic device generating heat during use. The device includes a toroidal electric motor with a centrifugal blower for directing air flow in a downward and outward direction, a heat sink positioned to receive the air flow from the blower; and a spiral diffuser as part of the heat sink, the diffuser having vanes for directing the air flow spirally over the heat sink. The vanes may include microfabricated vibrating reeds and a plurality of microfabricated dimples on at least some of the vanes.