A welded plate type air to liquid heat exchanger has a plurality of plates each with an internal volume inside a peripheral flange having a flange thickness. The plates are in parallel fluid communication with an inlet and outlet, and are mounted in a frame with a mutual predetermined distance, such that air flows therebetween. The plates are mounted between two plate holding frame members on opposite sides of the plates. The frame members have an exterior edge and slits in a comb-like shape extending from the exterior edge. First type and second type slits are provided in an alternating configuration. The first type are formed with a narrow entry passage section having a width corresponding to the flange thickness and a widened opening section therebehind. The first type receive the peripheral flanges of the plates in the narrow passage section. The second type are substantially straight and vacant.

The present invention relates to improved subsea or submerged cooler designs for subsea applications, and particularly to a unique pipe support arrangement (5, 16, 17, 18) in a submerged cooler (20), an improved submerged cooler frame (1) and an improved submerged cooler (20).

Negative-stiffness-producing mechanisms can be incorporated with structural devices that are used on spacecraft that provide thermal coupling between a vibrating source and a vibration-sensitive object. Negative-stiffness-producing mechanisms can be associated with a flexible conductive link (FCL) or “thermal strap” or “cold strap” to reduce the positive stiffness of the FCL. The negative-stiffness-producing mechanisms can be loaded so as to create negative stiffness that will reduce or negate the natural positive stiffness inherent with the FCL. The FCL will still be able to provide maximum thermal conductance while achieving low or near-zero stiffness to maximize structural decoupling.

A heat exchanger includes a housing with an inlet port, an outlet port, an interior facing surface defining a coolant channel, a first opening surrounded by an exterior facing surface, and a second opening defined by a first inner diameter. A tube assembly defines a plurality of exhaust gas flow channels and a plurality of coolant cross channels within the housing. A first diffuser directs a first fluid into the tube assembly and is joined to a first header plate, which separates the first fluid from a second fluid within the coolant channel. A second diffuser directs the first fluid out of the tube assembly. The second diffuser is located within the second opening and sealed to the second opening by seals around the second diffuser.

A heat exchanger includes: a first straight section; a second straight section; and a bent section or elbow linking the first straight section and the second straight section. Each straight section comprises a part of an internal cylindrical shell and of an external cylindrical shell, both cooperating to form an intershell space enclosing a bundle of parallel U-bent tubes having each a first and a second straight part respectively located in the first straight section and second straight section of the exchanger and a 180°-bent part located in the bent section or elbow of the exchanger, so that, in use, a first fluid to be heated and vaporized is flowing in the tubes. The external cylindrical shell is provided respectively at one end with an inlet and at another end with an outlet for a second fluid which is a hot thermal fluid.

A heat exchanger (HEX) arrangement for cooling air in a gas turbine engine is provided. The HEX arrangement may include a heat exchanger coupled to a plurality of ducts comprising a hot-side inlet duct and a hot-side outlet duct. The hot-side outlet duct may be in fluid communication with a compressor section of the gas turbine engine and in mechanical communication with a diffuser case. The HEX arrangement may further include a plurality of supporting links coupled between the heat exchanger and the gas turbine engine for securing the heat exchanger relative to the gas turbine engine. The supporting links may comprise a statically determined system. A spring rate ratio of between 1% and 30% may exist between the plurality of ducts and the plurality of supporting links.

A gas turbine engine recuperator recuperator including exhaust passages providing fluid flow communication between an exhaust inlet and an exhaust outlet, the exhaust inlet being oriented to receive exhaust flow from a turbine of the engine and the exhaust outlet being oriented to deliver the exhaust flow to atmosphere, the exhaust passages having an arcuate profile in a plane perpendicular to a central axis of the recuperator to reduce a swirl of the exhaust flow. Air passages are in heat exchange relationship with the exhaust passages and providing fluid flow communication between an air inlet and an air outlet, design to sealingly respective plenum of the gas turbine engine.

A heat exchange system includes a tubular fan air inlet portion and a tubular cooled air outlet portion connected to a first end of a tubular mid portion. The heat exchange system further includes a tubular hot air inlet portion and a tubular recycled fan air outlet portion connected a second end of the mid portion. Still further, the heat exchange system includes an integrally-formed, compliant heat exchanger tube extending between the hot air inlet portion and the cooled air outlet portion within the mid portion to define a heat exchanger first flow passage within the heat exchanger tube and a second flow passage outside of the heat exchanger tube but within the tubular mid portion. Methods for fabricating such heat exchange systems are also provided.

A heat exchanger with a heat-exchange core in which a first fluid and a second fluid circulate, at least one header tank configured to duct the second fluid from or to the heat-exchange core. The header tank has at least a shoulder oriented toward the outside of said header tank, and at least one header tank corner. At least one fastening member for fastening the header tank is positioned at least partly at the periphery of the heat-exchange core and includes at least one peripheral groove delimited by a base wall and a lateral wall and in which the shoulder of the header tank is at least partially housed. Part of the corner portion faces an upper face of the shoulder opposite to the groove of the fastening member and at a non-zero distance from this upper face so that a space is left between the corner portion and the upper face of the shoulder.

A system may include a turbine and a recuperative heat exchanger system. The recuperative heat exchanger system is configured to receive exhaust gases from the turbine. The recuperative heat exchanger system may include a precool section to cool the exhaust gases, a major heating section to receive the cooled the exhaust gases, and a minor heating section to receive the cooled the exhaust gases.