Aircraft bypass duct heat exchanger

A turbine engine comprising:

• one or more fan sections;
• one or more compressor sections aft and downstream of the one or more fan sections along a core flowpath;
• a combustor section downstream of the one or more compressor sections along the core flowpath;
• one or more turbine sections downstream of the combustor section along the core flowpath;
• a bypass flowpath;
• an inner case wall along the bypass flowpath and having a plurality of first ports and a plurality of second ports;
• an array of heat exchanger plates mounted to the inner case wall for providing heat transfer from a first flowpath to the bypass flowpath, wherein each plate has:
• first and second faces along the bypass flowpath;
• a proximal edge mounted to the inner case wall;
• an inlet along the proximal edge and mated to a respective one of the first ports;
• an outlet along the proximal edge and mated to a respective one of the second ports;
• and
• a branch segment of the first flowpath passing from the inlet to the outlet;
• and
• an outlet plenum, the inner case wall second ports open to the outlet plenum wherein:
• the first flowpath is a bleed flowpath branching from the core flowpath and rejoining the core flowpath after passing through the array of heat exchanger plates.