Patent ID: 8784047

Claim:
A gas turbine engine comprising: a core supported relative to a fan case, 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 configured to be shielded from a fan airflow and in fluid communication with the compressor section; and a heat exchanger having a plate extending a length and supporting fins that are arranged in the fan duct, the fins extending substantially the length in a longitudinal direction from a leading edge of the fin to a trailing edges of the fin, the leading and trailing edges respectively including first and second heights, the leading edge arranged upstream from the trailing edge, the first height less than the second height, the heat exchanger including first and second sides opposite one another, the first side including the fins configured to be exposed to the fan airflow flow, and the second side including another set of fins exposed to the bleed cavity and configured to be shielded from the fan airflow.