초록 ▼

An acoustic panel (26) for the nacelle (20) of a high bypass jet engine. The acoustic panel (26) has a perforated composite inner sheet (54), an outer composite sheet (96, 98), and a honeycomb-core material (74) sandwiched therebetween. The acoustic panel (26) includes an integral forward ring (36)

An acoustic panel (26) for the nacelle (20) of a high bypass jet engine. The acoustic panel (26) has a perforated composite inner sheet (54), an outer composite sheet (96, 98), and a honeycomb-core material (74) sandwiched therebetween. The acoustic panel (26) includes an integral forward ring (36) and integral wedge fairings (44).

대표청구항 ▼

[ What is claimed is:] [1.] A method of forming a forward ring integral with a composite panel, comprising the steps of:stacking an inner face sheet, a honeycomb core, and first outer face sheet on a lay-up mandrel;arranging composite material for an integral ring against the lay-up mandrel having a

[ What is claimed is:] [1.] A method of forming a forward ring integral with a composite panel, comprising the steps of:stacking an inner face sheet, a honeycomb core, and first outer face sheet on a lay-up mandrel;arranging composite material for an integral ring against the lay-up mandrel having a contour that substantially matches an intended final shape of the integral ring;placing a plug against the side of the composite material for the integral ring opposite of the contour of the lay-up mandrel;bagging the acoustic panel with a vacuum bag so that the vacuum bag is placed around and against the plug; andapplying to the vacuum bag during curing so that the plug presses the material for the integral ring in place.