Abstract: A system for reinforcing a substrate includes a rotary device, a first guide connected to the rotary device, and a form positioned against the first guide. A reinforcement is supplied to wind around the form and against the first guide. A method for reinforcing a substrate includes connecting a first guide to a rotary device and positioning a form on a first side of the first guide. The method further includes winding a reinforcement around the form and against the first side of the first guide.

Abstract: A turbine blade assembly is disclosed. In one embodiment, the turbine blade assembly may generally include a turbine blade having a root portion and an airfoil. The airfoil may extend radially from the root portion to an airfoil tip. Additionally, the turbine blade assembly may include a composite rod extending within the turbine blade. The composite rod may include a first end coupled to the airfoil at the airfoil tip and a second end coupled to the root portion. Moreover, the coefficient of thermal expansion of the composite rod may be designed to be less than or equal to the coefficient of thermal expansion of the airfoil.

Abstract: A system for reinforcing a substrate includes a rotary device, a first guide connected to the rotary device, and a form positioned against the first guide. A reinforcement is supplied to wind around the form and against the first guide. A method for reinforcing a substrate includes connecting a first guide to a rotary device and positioning a form on a first side of the first guide. The method further includes winding a reinforcement around the form and against the first side of the first guide.

Abstract: A process of forming a material having nano-particles and a material having nano-particles are disclosed. The process includes arranging nano-particles in a predetermined pattern within a matrix material. The material includes arranged nano-particles forming a predetermined pattern in the matrix material.

Abstract: Aspects of the invention provide for an aperture reinforcement structure. In one embodiment, a composite laminate is disclosed, including: a first sheet of material having a first aperture therein; a second sheet of material having a second aperture therein corresponding to the first aperture; and a reinforcement structure having: a continuous fiber including a plurality of convolutions affixed to at least one of the first sheet of material or the second sheet of material, the plurality of convolutions surrounding at least one of the first aperture or the second aperture; and a resin binding the plurality of convolutions to one another.

Abstract: A support apparatus for a gas turbine shroud is disclosed. The apparatus includes an outer shroud block having a coupling connectable to a casing of the gas turbine and a shroud component having a forward flange and an aft flange. The shroud component is attached to the outer shroud block via the forward flange and the aft flange. The apparatus further includes a damper disposed between the outer shroud block and the shroud component and a biasing element disposed within the outer shroud block. A translational degree of freedom between the damper and the outer shroud block defines a direction of motion of the damper. The biasing element is in operable connection between the outer shroud block and the shroud component via the damper, a bias force of the biasing element directed along the direction of motion of the damper.

Abstract: A nozzle for a turbine includes a duct member having a substantially uniform wall thickness. Nozzles made of different materials can be used.

Abstract: Disclosed is a coated substrate including a substrate coating applied to at least one substantially flat surface of the substrate, the coating including at least one of an axial concavity and a circumferential curvature, the substrate being configured for disposal parametrically about a moving component.

Abstract: Disclosed is a coated substrate including a substrate coating applied to at least one substantially flat surface of the substrate, the coating including at least one of an axial concavity and a circumferential curvature, the substrate being configured for disposal parametrically about a moving component.

Abstract: A method facilitates the assembly of a turbine engine. The method includes providing a shroud support block having a forward end and an aft end, coupling a forward end of a shroud to the shroud support block using a forward fastener, and coupling an aft end of the shroud to the shroud support block using an aft fastener. The method also includes installing a locking pin through the aft fastener to retain the aft fastener, and staking the locking pin in the shroud support block, such that the locking pin is securely coupled to the shroud support block.

Abstract: A support apparatus for a gas turbine shroud is disclosed. The apparatus includes an outer shroud block having a coupling connectable to a casing of the gas turbine and a shroud component having a forward flange and an aft flange. The shroud component is attached to the outer shroud block via the forward flange and the aft flange. The apparatus further includes a damper disposed between the outer shroud block and the shroud component and a biasing element disposed within the outer shroud block. A translational degree of freedom between the damper and the outer shroud block defines a direction of motion of the damper. The biasing element is in operable connection between the outer shroud block and the shroud component via the damper, a bias force of the biasing element directed along the direction of motion of the damper.