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.

A film stack made from compacted green films and capable of being sintered to form a ceramic component with monolithic multi-layer structure is disclosed. The film stack includes a functional layer comprising a green film comprising a functional ceramic and a tension layer comprising a green film comprising a dielectric material. The tension layer is directly adjacent to the functional layer in the multi-layer structure. The multilayer structure also includes a first metallization plane and second metallization plane. The functional layer is between the first metallization plane and the second metallization plane.

A production method for a ceramic matrix composite is comprised of: compounding an aggregate powder including a ceramic and a binder including at least one of thermoplastic resins and waxes to form a composition of the aggregate powder and the binder; pressing the composition to form sheets; accumulating fabrics of reinforcement fibers including the ceramic and the sheets alternately; pressing an accumulated body of the fabrics and the sheets; and generating a matrix combining the reinforcement fibers together.

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.

An electrochemical sensor comprising a probe immersible in a measured medium and having at least two electrodes of a first electrically conductive material and at least one probe body of a second, electrically non-conductive material. The electrodes are at least partially embedded in the probe body and insulated from one another by the probe body, wherein the at least two electrodes are embodied of at least one conductive material and the probe body of at least one electrically insulating ceramic, wherein the electrodes are embodied of thin, measuring active layers of a conductive material and sit in an end face of the probe body of a ceramic material, and wherein the electrodes are electrically contacted via connection elements extending through the probe body.

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 method for manufacturing a turbine nozzle vane made of ceramic matrix composite material, wherein the vane is manufactured using a first fibrous preform including a hollow central section intended to form a fibrous reinforcement of an airfoil of the vane to be obtained, and a pair of second fibrous preforms each having an opening with a shape of the airfoil of the vane to be obtained.

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 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, 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.