Methods of manufacturing composite sandwich components (100) and composite sandwich components overcome drawbacks in the prior art. For example, the large number of resin filled perforations that are unavoidable when manufacturing prior art composite sandwich components is avoided.

The present invention provides a laminated plate capable of not only achieving a reduced weight and an increased rigidity but also improving a sound absorbing performance, and a method for manufacturing the same. A laminated plate (1) is supposed to include a core layer (2) including a plate-shaped paper honeycomb structure (4) and a pair of fiber reinforcement layers (3) sandwiching the paper honeycomb structure (4) from both sides in a thickness direction and integrated with the paper honeycomb structure 4. The through-holes (5) of the paper honeycomb structure (4) are filled with a foam resin (6), and the core layer (2) is made up of the paper honeycomb structure 4 and the foam resin (6) filled in the through-holes (5). When the foam resin (6) is filled in the through-holes (5) of the paper honeycomb structure (4), the foam resin plate (6A) is pushed into the through-holes (5) as a filling material by utilizing a compression force of a mold (11).

The present invention provides a laminated plate capable of not only achieving a reduced weight and an increased rigidity but also improving a sound absorbing performance, and a method for manufacturing the same. A laminated plate (1) is supposed to include a core layer (2) including a plate-shaped paper honeycomb structure (4) and a pair of fiber reinforcement layers (3) sandwiching the paper honeycomb structure (4) from both sides in a thickness direction and integrated with the paper honeycomb structure 4. The through-holes (5) of the paper honeycomb structure (4) are filled with a foam resin (6), and the core layer (2) is made up of the paper honeycomb structure 4 and the foam resin (6) filled in the through-holes (5). When the foam resin (6) is filled in the through-holes (5) of the paper honeycomb structure (4), the foam resin plate (6A) is pushed into the through-holes (5) as a filling material by utilizing a compression force of a mold (11).

A ready to use surface veil and surface film integrated prepreg layer suitable to use in a production of lightweight structural parts/panels with class A surfaces includes a curable bottom base resin formulation including a curable bottom base resin, at least one first toughening agent, at least one accelerator, at least one curing agent and at least one hardener. The prepreg layer further includes a release paper coated with the curable bottom base resin formulation to obtained curable bottom base resin formulation coated release paper as a first resin film; a reinforcement fabric; an outer resin formulation including an outer resin, wherein the outer resin is the curable bottom base resin being 10% more viscous than a resin, at least one thermoplastic toughening agent, at least one accelerator, at least one curing agent and at least one hardener agent.

A multilayered cushion pad and a method for manufacturing the same are provided. The multilayered cushion pad includes a first woven fabric, a second woven fabric, and a first buffering layer. The first buffering layer is disposed between the first woven fabric and the second woven fabric. A material of the first woven fabric includes a poly-p-phenylene benzobisoxazole fiber, and a material of the second woven fabric is selected from the group consisting of: a poly-p-phenylene benzobisoxazole fiber, a polyphenylene sulfide fiber, a polybenzimidazole fiber, a ceramic fiber, a basalt fiber, an alkaline metal fiber, a silicic acid fiber, and a combination thereof. A material of the first buffering layer is selected from the group consisting of: a silicone rubber resin, a fluororubber resin, a polyvinylidene difluoride resin, a polyetheretherketone resin, a polyimide resin, a polyamide-imide resin, and a combination thereof.

A substrate holding board includes a first layer and a second layer forming an interfacial surface with the first layer. The first layer and the second layer contain diamond-like carbon. A refractive index of the first layer in a wavelength is higher than a refractive index of the second layer in the wavelength. A distance from the second layer to a topmost surface of the substrate holding board is smaller than a thickness of the first layer.

A substrate holding board includes a first layer and a second layer forming an interfacial surface with the first layer. The first layer and the second layer contain diamond-like carbon. A refractive index of the first layer in a wavelength is higher than a refractive index of the second layer in the wavelength. A distance from the second layer to a topmost surface of the substrate holding board is smaller than a thickness of the first layer.

This disclosure includes sandwich composites comprising fiber-reinforced laminates. The disclosure further includes one or more film adhesives between a core and the fiber-reinforced laminates.

Airfoils for gas turbine engines are provided. In one embodiment, an airfoil formed from a ceramic matrix composite material includes opposite pressure and suction sides extending radially along a span and defining an outer surface of the airfoil. The airfoil also includes opposite leading and trailing edges extending radially along the span. The pressure and suction sides extend axially between the leading and trailing edges. The leading edge defines a forward end of the airfoil, and the trailing edge defining an aft end of the airfoil. Further, the airfoil includes a trailing edge portion defined adjacent the trailing edge at the aft end of the airfoil; a plenum defined within the airfoil forward of the trailing edge portion; and a cooling passage defined within the trailing edge portion proximate the suction side. Methods for forming airfoils for gas turbine engines also are provided.

Airfoils for gas turbine engines are provided. In one embodiment, an airfoil formed from a ceramic matrix composite material includes opposite pressure and suction sides extending radially along a span and defining an outer surface of the airfoil. The airfoil also includes opposite leading and trailing edges extending radially along the span. The pressure and suction sides extend axially between the leading and trailing edges. The leading edge defines a forward end of the airfoil, and the trailing edge defining an aft end of the airfoil. Further, the airfoil includes a trailing edge portion defined adjacent the trailing edge at the aft end of the airfoil; a plenum defined within the airfoil forward of the trailing edge portion; and a cooling passage defined within the trailing edge portion proximate the suction side. Methods for forming airfoils for gas turbine engines also are provided.