Aircraft heat exchanger panel array interconnection

A gas turbine engine comprising:

• a fan, a compressor, a combustor, and a turbine;
• a core flowpath through the compressor, the combustor, and the turbine;
• a bleed flowpath branching from the core flowpath;
• a bypass flowpath bypassing the compressor, the combustor, and the turbine;
• and
• a heat exchanger for providing thermal energy transfer between a first flow along the bleed flowpath and a second flow along the a bypass flowpath, the heat exchanger comprising:
• at least one plate bank comprising a plurality of plates, each plate having:
• a first face and a second face opposite the first face;
• a leading edge along the bypass flowpath and a trailing edge along the bypass flowpath;
• a proximal edge having at least one inlet port along the bleed flowpath and at least one outlet port along the bleed flowpath;
• and
• at least one passageway along the bleed flowpath;
• an inlet manifold having at least one inlet port and at least one outlet port;
• an outlet manifold having at least one outlet port and at least one inlet port, the first flowpath passing from the at least one inlet port of the inlet manifold, through the at least one passageway of each of the plurality of plates, and through the at least one outlet port of the outlet manifold;
• and
• means linking distal portions of the plates for providing frictional damping.