Integral engine inlet frame air-cooled oil cooling apparatus

A gas turbine engine comprising:

• an inlet frame including an inlet plenum at a first end of an inlet frame flow path, the inlet frame defining an airflow entrance to a compressor, the inlet plenum defined by an inner radius and an outer radius, the outer radius defined by a surface of the inlet frame;
• the compressor to provide an airflow through the inlet frame;
• a pump to circulate a fluid;
• a plurality of struts supporting the inlet frame flow path, the plurality of struts to form an inner body at the inner radius of the inlet plenum, the outer radius of the inlet plenum to surround the inner body;
• and
• a fluid core connected to the pump and built at least partially into the inlet frame of the gas turbine engine, the fluid core to route the fluid through the inlet plenum.