Gas turbine engine heat exchanger fins with periodic gaps

摘要

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.

主权项

1. A gas turbine engine comprising:
a core supported relative to a fan case by the core including a core nacelle, and a fan duct provided between the core nacelle and the fan case, wherein the core includes a compressor section and a bleed cavity is provided within the core and in fluid communication with the compressor section; an actuation system component arranged within the bleed cavity, the actuation system component configured to actuate variable stator vanes in the compressor section; and a heat exchanger including first and second sides opposite one another, the second side including a set of rows of fins exposed to the bleed cavity, the set of fins having gaps between discrete fins in a given row.