Patent attributes
A heat exchanger for a gas turbine engine is provided by a structure including an enclosed fluid cavity. The structure has opposing sides, and a set of fins is supported on one of the sides and arranged outside the cavity. The set of fins includes rows of discrete chevron fins separated by periodic gaps. In one application, the heat exchanger is arranged in a gas turbine engine. A core is supported relative to a fan case by structure. A fan duct is provided between a core nacelle and a fan case. The core includes a compressor section and a bleed cavity is provided within the core and is in fluid communication with the compressor section. The heat exchanger includes first and second sides opposite one another. The second side includes the set of rows of fins with the periodic gaps exposed to the bleed cavity.
