Patent ID: 6051302
Filing Date: 2000-04-18
Classification: B29C,B32B,E04C,F01D,F02K,F05D,Y02T,Y10T

Abstract:
A corrosion-free thrust reverser inner wall for a jet engine, the engine having a hot engine housing and a surrounding annular duct for cold airflow, the inner wall being adapted for exposure up to 1100.degree. F. being adapted to be free from corrosion, being laminated and having in order, (a) a first layer of resin impregnated carbon fabric; (b) a first layer of adhesive adjacent one side of the fabric; (c) a non-metallic, thermally conductive honeycomb core having adequate thermal conductivity so that engine fan air passing over the inner wall carries away sufficient heat from the engine to the surrounding annular duct to minimize the need for insulation on the engine side of the inner wall, the cell walls of the honeycomb being reinforced with pitch-based carbon fibers; (d) a second layer of reticulated adhesive on the honeycomb core; and (e) a sound reducing layer of perforated, resin impregnated carbon fabric adjacent to the second layer of adhesive adapted to maintain proper acoustic properties, the laminated layers defining a composite sandwich panel having a thermally conductive honeycomb core.