A polar functional group is added onto a surface of a metallic member. A resin member contains an adhesive functional group. The adhesive functional group and the polar functional group attract each other. A method for joining the metallic member and the resin member to each other includes: heating a junction between the metallic member and the resin member while pressing the metallic member and the resin member against each other with a first load; maintaining temperature of the junction higher than melting temperature of a resin that structures the resin member while pressing the metallic member and the resin member with each other with a second load smaller than the first load; and cooling the junction to temperature lower than the melting temperature while pressing the metallic member and the resin member against each other with a third load larger than the second load.

A heat radiating member includes: a composite portion composed of a composite material which contains particles of a satisfactorily thermally conductive material in a metal matrix; and a metal layer formed on at least one surface of the composite portion and composed of a metal. A method for producing a heat radiating member includes: a preparation step to prepare a composite material which contains particles of a satisfactorily thermally conductive material in a metal matrix; a powder arrangement step to dispose a metal powder composed of metal particles on at least one surface of the composite material; and a heating step to heat the composite material and the metal powder, with the metal powder disposed on the composite material, to form a metal layer composed of a metal of the metal powder on a composite portion composed of the composite material.

A heat radiating member includes: a composite portion composed of a composite material which contains particles of a satisfactorily thermally conductive material in a metal matrix; and a metal layer formed on at least one surface of the composite portion and composed of a metal. A method for producing a heat radiating member includes: a preparation step to prepare a composite material which contains particles of a satisfactorily thermally conductive material in a metal matrix; a powder arrangement step to dispose a metal powder composed of metal particles on at least one surface of the composite material; and a heating step to heat the composite material and the metal powder, with the metal powder disposed on the composite material, to form a metal layer composed of a metal of the metal powder on a composite portion composed of the composite material.

A heat transfer device includes a first and second substrate, and a heat transfer layer. The first substrate includes a first plate and a first adhesive layer that is formed on the first plate. The second substrate includes a second plate and a second adhesive layer that is formed on the second plate. The heat transfer layer is sandwiched between the first adhesive and second adhesive layers, and includes a plurality of carbon flakes that is made from one of graphene or graphite. The carbon flakes lies on the first adhesive layer with partial overlap of the carbon flakes.

A technique to additively print onto a dissimilar material, especially ceramics and glasses (e.g., semiconductors, graphite, diamond, other metals) is disclosed herein. The technique enables manufacture of heat removal devices and other deposited structures, especially on heat sensitive substrates. It also enables novel composites through additive manufacturing. The process enables rapid bonding, orders-of-magnitude faster than conventional techniques.

A hypersonic aircraft includes one or more leading edge assemblies that are designed to manage thermal loads experienced at the leading edges during high speed or hypersonic operation. Specifically, the leading edge assemblies may include an outer wall tapered to a leading edge or stagnation point. The outer wall may define a vapor chamber and a capillary structure within the vapor chamber for circulating a working fluid in either liquid or vapor form to cool the leading edge. In addition, a thermal energy storage reservoir positioned within the vapor chamber contains a phase change material for absorbing thermal energy.

A hypersonic aircraft includes one or more leading edge assemblies that are designed to manage thermal loads experienced at the leading edges during high speed or hypersonic operation. Specifically, the leading edge assemblies may include an outer wall tapered to a leading edge or stagnation point. The outer wall may define a vapor chamber and a capillary structure within the vapor chamber for circulating a working fluid in either liquid or vapor form to cool the leading edge. In addition, a thermal energy storage reservoir positioned within the vapor chamber contains a phase change material for absorbing thermal energy.

A syngas loop boiler includes a casing that surrounds a tube bundle, wherein the tube bundle includes a plurality of tubes. One end of each of the tubes is joined to a tube-sheet provided with corresponding tube-sheet inlet holes for inletting the syngas in the boiler, wherein each tube-sheet inlet hole is internally provided with at least a protective sleeve welded at both ends to corresponding surfaces of the tube-sheet inlet hole. Each tube-sheet inlet hole is provided with a first respective weld overlay placed at the inlet mouth of the tube-sheet inlet hole, so that a first end of each protective sleeve is welded to the first weld overlay. Each tube-sheet inlet hole is internally provided with at least a bore groove that contains a respective in-bore second weld overlay, so that the second end of the protective sleeve is welded to the in-bore second weld overlay. Each protective sleeve is thus welded at both ends to respective weld overlays, with the possibility of removal and re-installation without performing any post weld heat treatment.

A syngas loop boiler includes a casing that surrounds a tube bundle, wherein the tube bundle includes a plurality of tubes. One end of each of the tubes is joined to a tube-sheet provided with corresponding tube-sheet inlet holes for inletting the syngas in the boiler, wherein each tube-sheet inlet hole is internally provided with at least a protective sleeve welded at both ends to corresponding surfaces of the tube-sheet inlet hole. Each tube-sheet inlet hole is provided with a first respective weld overlay placed at the inlet mouth of the tube-sheet inlet hole, so that a first end of each protective sleeve is welded to the first weld overlay. Each tube-sheet inlet hole is internally provided with at least a bore groove that contains a respective in-bore second weld overlay, so that the second end of the protective sleeve is welded to the in-bore second weld overlay. Each protective sleeve is thus welded at both ends to respective weld overlays, with the possibility of removal and re-installation without performing any post weld heat treatment.

A diffuser plate for a thermal transfer device can include a body having a number of first apertures and a second aperture that traverse therethrough, where the first apertures are asymmetrically arranged with respect to the second aperture. The first apertures can have a first shape and a first size, and where the first apertures are configured to receive a plurality of tubes. The second aperture has a second size, where the second size is larger than the first size.