Method for transferring heat in an aircraft engine thrust reverser
AssigneeThe Boeing Company
InventorFrancis W. Moore
Life of this patent
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Abstract
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.
Claims3
In an aircraft power plant, a method for conducting heat through a thrust reverser inner wall made from a honeycomb core sandwich panel, comprising the steps of:
- (a) conducting heat from a carbon-fiber reinforced resin composite face sheet of the inner wall to a carbon fiber honeycomb core, the core having oriented carbon pitch fibers and a thermal conductivity of about 1.09-2.05W/m−°K;
- and
- (b) conducting heat from the core to a perforated, fiber reinforced resin composite face sheet in contact with fan airflow for the aircraft power plant.
A method for transferring heat from an aircraft engine to engine fan air in an engine nacelle, comprising the steps of:
- (a) orienting pitch based carbon fibers in a thrust reverser inner wall positioned between the engine and the fan air;
- (b) conducting heat from the engine to the fan air through the fibers to a perforated carbon fiber top layer;
- and
- (c) transferring heat from the top layer to the air passing over the top layer.
A method for reducing weight in a thrust reverser inner wall for an aircraft engine, comprising the step of:
- reducing the volume of insulation for the inner wall by using pitch based carbon fibers in a honeycomb core of the wall rather than aluminum honeycomb to conduct heat from the engine to engine fan air to cool the wall and the engine.
Dependencies are inferred from the claim text.