A precast composite wall structure and method for forming the wall structure are disclosed. The method includes providing a casting bed defining a plurality of shapes corresponding to a three-dimensional outer surface of a wall structure, placing a first layer of uncured concrete to conform to the shapes defined by the lower surface, positioning a forming member in overlying relation above the frame, the forming member defining a plurality of rectangular-shaped channels therebetween, positioning a stud frame within the casting bed along the forming member, placing a second layer of uncured concrete within the casting bed to conform to the rectangular-shaped channels between the rectangular protrusions, and allowing the concrete to cure.

Pre-stressed insulated concrete panels are disclosed. Methods of making and using pre-stressed insulated concrete panels are also disclosed.

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.

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.

A lid for a utilities vault having a moldable core and a reinforcement matrix positioned within the core, the reinforcement matrix including longitudinally and laterally extending intersecting members and a plurality of lid feature housings positioned on and attached to the intersecting members, the lid feature housings extending through the core and protruding to the upper and lower surfaces of the lid, and the plurality of longitudinally and laterally extending intersecting members have a height sufficient to provide reinforcement without a perimeter member for the reinforcement matrix.

A precast concrete wall panel and system comprising pre-stressed concrete layers surrounding an insulation layer, the concrete layers prestressed using fiber reinforce polymer bar rebar.

A use of at least one form insert for in-situ manufacture of a hollow core or hollow core analogue slab, the at least one form insert positioned in a mould defining a monolithic volume in which the hollow core or hollow core analogue slab is manufactured by pouring a cement-based curable material into the monolithic volume to submerge the at least one form insert.

Improved tilt-up and precast construction panels and improved methods for creating the same address deficiencies in the current tilt-up and precast construction panels. Improved tilt-up and precast construction panels use less concrete and less steel reinforcement and weigh less than current tilt-up and precast construction panels. Additionally, improved tilt-up and precast construction panels have greater insulative properties (both heat and sound) than do current tilt-up and precast construction panels. Improved tilt-up and precast construction panels require less labor on the construction site, thereby increasing efficiency and profitability of construction crews. Additional advantages of implementations of the invention will become apparent through the following description and by practice of implementations of the invention.

A method of forming an article including: contacting a fugitive tool with a powdered parent material; densifying the powdered material; and destructively removing the fugitive tool. A coating of a different material may be formed against the parent material using a similar approach.