Importance

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Abstract

A panel for a nacelle structure that surrounds a jet engine core includes a longitudinally extending, generally semicircular center region, an upper bifurcation region, a lower bifurcation region, a hinge beam region extending from the upper bifurcation region and configured to receive an upper thrust reverser track guide, and a latch beam region extending from the lower bifurcation region and configured to receive a lower thrust reverser track guide. A bypass duct is formed in a space between the panel and the nacelle structure. A hinge beam structure and latch beam structure are integrally formed with the panel. An inner skin layer extends continuously across a bond panel surface generally facing the engine core and an outer skin layer extends continuously across a bond panel surface generally facing the bypass duct, the inner and outer skin layers extending across the center region, upper and lower bifurcation regions, hinge beam region, and latch beam region. The outer skin layer may have an acoustic treatment, such as being perforated in at least the center region and the upper and lower bifurcation regions. In this way, a separate hinge beam and latch beam are not used, and therefore there is no need to couple the panel to the respective beams.

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First Claim