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.

Described herein are hard armor plate comprising a first molded plate of a plurality of ballistic fibers, a second molded plate of a plurality of ballistic fibers, and a layer of ceramic tiles adhered to the first molded plate and the second molded plate, wherein the layer of ceramic tiles is between the first molded plate and the second molded plate; and methods of making hard armor plates.

Composite materials include a steel matrix with reinforcing carbon fiber formed of individual fibers penetrating into the matrix to substantial depth. The fibers typically have defined diameters and large ratios of penetration depth to fiber diameter. Specified methods for forming the composite materials have a unique ability to achieve the large ratios of penetration depth to fiber diameter.

Composite materials include a steel matrix with reinforcing carbon fiber integrated into the matrix. The composite materials have substantially lower density than steel, and are expected to have appreciable strength. Methods for forming composite steel composites includes combining a reinforcing carbon fiber component, such as a woven polymer, with steel nanoparticles and sintering the steel nanoparticles in order to form a steel matrix with reinforcing carbon fiber integrated therein.

Composite materials include a steel matrix with reinforcing carbon fiber integrated into the matrix, and having unreinforced regions suitable for stamping or other deformation. The composite materials have substantially lower density than steel, and are expected to have appreciable strength within regions having the reinforcing carbon fiber, while having greater deformability in unreinforced regions. Methods for forming composite steel composites includes combining at least two laterally spaced apart reinforcing carbon fiber components, such as a carbon fiber weave, with steel nanoparticles and sintering the steel nanoparticles in order to form a steel matrix with reinforcing carbon fiber integrated therein, and unreinforced regions located in the lateral spaces between carbon fiber components.

In an aspect, a cap liner comprises a sintered fluoropolymer layer; and a backing layer; wherein the sintered fluoropolymer layer is in direct physical contact with the backing layer with no intervening layer located there between. In another aspect, a method of forming the cap liner of comprises plasma etching the sintered fluoropolymer layer to form a sintered plasma etched layer; and laminating the sintered plasma etched layer and the backing layer to form the cap liner.

A composite fabric laminate can include an open mesh fabric, a first continuous film comprising a fluoropolymer, and a second continuous film comprising a fluoropolymer. The fluoropolymer of the first continuous film and the fluoropolymer of the second continuous films can be in direct contact with one another. A method of forming a composite fabric laminate that includes disposing an open mesh fabric between a first continuous film and a second continuous film, each comprising an at least partially unsintered fluoropolymer film, to form a composite; laminating the composite at a pressure of at least 100 psig and a temperature of no greater than 350 C.; and sintering the laminated composite to form the composite fabric laminate.

A flame arrester comprising two part-bodies, which consist of different wire fabric layers and are connected to one another by an intermediate layer of particularly coarse-meshed wire fabric. The coarse-meshed wire fabric preferably consists of a thick wire. Both the wire diameter and the mesh width of this intermediate layer are preferably much greater than the mesh widths and wire diameters of the wires used for the part-bodies. The pressure relief body combines a high degree of mechanical stability with a great flame arresting capability and at the same time very low flow resistance.

Ceramic matrix composite airfoils for gas turbine engines are provided. In an exemplary embodiment, an airfoil includes opposite pressure and suction sides extending radially along a span. The pressure and suction sides define an outer surface of the airfoil. The airfoil further includes opposite leading and trailing edges extending radially along the span, the pressure and suction sides extending axially between the leading and trailing edges. The airfoil also includes a filler pack defining the trailing edge; the filler pack comprises a ceramic matrix composite material. Moreover, the airfoil includes a plenum defined within the airfoil for receiving a flow of cooling fluid, and a cooling passage defined within the filler pack for directing the flow of cooling fluid from the plenum to the outer surface of the airfoil. 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.