A Co-based alloy heat exchanger comprises: in mass %, 0.08-0.25% C; 0.1% or less B; 10-30% Cr; 5% or less Fe and 30% or less Ni, the total amount of Fe and Ni being 30% or less; W and/or Mo, the total amount of W and Mo being 5-12%; Ti, Zr, Nb and Ta, the total amount of Ti, Zr, Nb and Ta being 0.5-2%; 0.5% or less Si; 0.5% or less Mn; 0.003-0.04% N; and the balance being Co and impurities. The impurities include 0.5% or less Al, and 0.04% or less O. The heat exchanger is a polycrystalline body of matrix crystal grains with an average size of 5-100 μm. In the matrix crystal grains, segregation cells with an average size of 0.13-2 μm are formed, wherein components constituting an MC type carbide comprising Ti, Zr, Nb and/or Ta are segregated in boundary regions of the segregation cells.

An environmental control system is provided including a ram air circuit having a ram air duct and at least one heat exchanger arranged within the ram air duct. The ram air duct is curved about a ram axis. A compression device includes a compressor and at least one turbine operably coupled by a shaft rotatable about a shaft axis. The ram axis is arranged coaxially with the shaft axis.

Devices and methods for fabrication of a multiscale porous high-temperature heat exchanger for high-temperature and high-pressure applications are disclosed. The heat exchanger can include a core with macrochannels formed in a checkerboard pattern to facilitate alternative flow of working fluid having hot and cold temperatures between adjacent macrochannels. Each macrochannel can include a two-dimensional microchannel array that further distributes flow throughout the heat exchanger to enhance heat transfer and mechanical strength without significant pressure drop penalty. The heat exchanger can further include a header integrated therewith to distribute working fluid flowing through the heat exchanger through the outlets such that it flows evenly therethrough. Methods of fabricating heat exchangers of this nature are also disclosed.

A recuperator disposed in the exhaust duct of a gas turbine engine includes a plurality of recuperator plates arranged in a spaced-apart relationship to define therebetween a plurality of interstices and fluid channels, the plurality of interstices adapted to direct therethrough at least one first stream received at a leading plate edge of the recuperator plates and the plurality of fluid channels adapted to direct therethrough at least one second stream to effect heat exchange between the at least one first stream and the at least one second stream. Each recuperator plate includes, formed at the leading plate edge thereof, a first concavity extending along the leading edge in a direction substantially parallel to a longitudinal axis of the plate. The first concavity extends transversely to a direction of the at least one first stream flowing over each recuperator plate.

A heat exchanger is provided. The heat exchanger is formed of a spiral wound flow body (70) having a plurality of passages (76) ending therethrough for passage of a first fluid. The flow body is positioned within a housing (42) and a cross-flow of a second fluid passes between or across successive layers of the spiral wound flow body. The intermixing of the thermal energy of the cross-flowing second fluid and the first fluid provide improved heat exchange.

A heat exchanger system includes a core structure with an oil flow path configured to receive an oil flow. The heat exchanger system also includes a fuel flow path included in the core structure and configured to receive a fuel flow. The fuel flow path is coupled to the oil flow path to allow the fuel flow to receive heat from the oil flow in the oil flow path. Also, the heat exchanger system includes a supplemental airflow path defined at least partly by the core structure and configured to receive a supplemental airflow that receives heat from at least one of the oil flow and the fuel flow.

An outlet manifold is provided and includes an outlet portion having first and second sides and an inlet portion to which the outlet portion is fluidly coupled. The inlet portion has first and second sides corresponding to the first and second sides of the outlet portion. Each of the first and second sides of the inlet portion includes one or more tubular members connectable with corresponding tube joints and a mixing chamber fluidly interposed between each of the one or more tubular members and the outlet portion.

A fan casing assembly, connection assembly and method for moving a fan casing cooler. The fan casing assembly for the turbine engine can include an annular fan casing with a peripheral wall having a flow path defined through the casing. A fan casing cooler can mount along the peripheral wall in order to confront a cooling fluid flow within the flow path in order to cool a fluid through the fan casing cooler.

A heat exchanger includes a separator member that divides a first flow passage from a second flow passage. The heat exchanger also includes a plurality of first hollow members that extend across the first flow passage at respective non-orthogonal angles. The plurality of first hollow members are fluidly connected to the second flow passage. Moreover, the heat exchanger includes a plurality of second hollow members that extend across the second flow passage at respective non-orthogonal angles. The plurality of second hollow members are fluidly connected to the first flow passage.

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.