Method for transferring heat in an aircraft engine thrust reverser

A typical commercial airplane gas turbine engine includes a thrust reverser cowling nacelle. The nacelle structure consists of an inner and outer cowl joined with bifurcations. The engine fan airstream runs through the annular cavity between the two cowls. The inner cowl or wall covers the engine case, accessories, and ducting installed therein. Because the engine case is very hot, up to 1100 degrees F., the inside surface of the inner cowl, referred to as the thrust reverser inner wall, is exposed to high radiative energy. Thrust reverser inner wall structure comprising a thermally conductive nonmetallic carbon pitch fiber honeycomb core sandwiched between a top and bottom layer. The core is adhered by a reticulated layer of adhesive to a perforated carbon fiber top layer, and adhered to a base layer of nonmetallic, nonperforated carbon fiber reinforced fabric.