Disclosed are a method for manufacturing a high-temperature structural material and a precursor. The method includes following operations: providing a precursor, wherein the precursor is made of a polymer or the polymer and a high-temperature material; processing the precursor into a precursor object with a preset shape; and converting the processed precursor object into a high-temperature material object through a preset processing method.

A gas turbine engine component includes a gas turbine engine component body formed of a ceramic matrix composite material having at least one fastener integrally formed with the gas turbine engine component body as a single-piece structure. The gas turbine engine component body initially comprises a rigidized preform structure formed from a polymer based material. The at least one fastener connects the gas turbine engine component body to an engine support structure.

A part for an aircraft turbojet engine nacelle is made of a composite material and includes at least one outer face (S1), a fibrous preform including fiber locks and having a surface(s) delimiting depressions between fiber locks, a covering material which at least partially covers the surface(s) of the fibrous preform and in particular the depressions, and a matrix which binds entirely the covering material and the fibrous preform. The covering material is a fibrous mat and the outer face (S1) is smooth. A method for manufacturing such a part includes manufacturing the fibrous preform, providing a fibrous mat, depositing the fibrous preform and fibrous mat in a mold, dispersing the matrix between the fibers of the preform and mat and consolidating the fibrous preform and mat.

A manufacturing method of a honeycomb structure including: a formed body forming step of extruding a forming raw material, to form a plurality of quadrangular prismatic columnar honeycomb formed bodies; a firing step of firing the honeycomb formed bodies, to form a plurality of quadrangular prismatic-columnar quadrangular segments; a triangular segment forming step to form a triangular prismatic-columnar triangular segment; a bonded body forming step to form a honeycomb bonded body; and a circumference grinding step to manufacture the honeycomb structure, wherein the bonded body forming step further includes: a pressurizing step of pressurizing the triangular segment from a circumferential direction of the temporary assembly toward a central direction thereof, by use of a pressurizing jig comprising a pressurizer.

Provided is a building material that is lightweight, exhibits excellent formability, and is inhibited from being damaged during transportation, and a method for producing the same. Specifically, provided is a method for producing a building material, including: a first step of curing a core layer material including a hydraulic material, a silica-containing material, and an aluminum powder, to react the aluminum powder and form bubbles, and incompletely hardening the hydraulic material and the silica-containing material, to form a foamed core layer; a second step of dispersing a surface layer material including a hydraulic material, and a silica-containing material, to form an unfoamed surface layer; a third step of stacking the foamed core layer on the unfoamed surface layer, to form a stack including the unfoamed surface layer and the foamed core layer; and a fourth step of pressing and curing the stack, and a building material produced therewith.

Laminate components and methods for forming the same are provided. In one exemplary aspect, one or more features are laser cut into or along a laminate component or laminate sections thereof. The features are laser cut into or along the laminate component in an atmosphere. In this manner, and oxide layer is formed on the laser cut surfaces of the future. The features are laser cut into or along the laminate component or laminate sections thereof prior to an infiltration process, such as melt infiltration or chemical vapor infiltration. Accordingly, when the laminate component is infiltrated with an infiltration material, the infiltration material is prevented from infiltrating therethrough.

A composite ceramic element and method of firing clay or ceramic elements in a roller kiln, comprising the steps of passing a first ceramic element on rollers through the roller kiln, passing a second ceramic element on rollers through the roller kiln, and mating and securing the first and second ceramic elements together after passing each said ceramic element through the roller kiln.

A turbine blade having an airfoil portion includes a first ceramic matrix composite (CMC) component having a first outer surface and a second ceramic matrix composite (CMC) component having a second outer surface. The second CMC component is positioned adjacent the first CMC component such that the first outer surface and the second outer surface align with one another and at least partially define the airfoil portion. A ceramic bead is at least partially formed at an interface between the first CMC component and the second CMC component. The formation of the bead melts a portion of the first CMC component and the second CMC component, such that the ceramic bead, the first CMC component, and the second CMC component become a single contiguous component and the bead fixedly attaches the first CMC component and the second CMC component. The bead includes a bead outer surface that extends outward beyond the first outer surface and the second outer surface and an overlayer is deposited onto the airfoil portion, the overlayer bonded to the first outer surface, the second outer surface, and the bead outer surface.

A manufacturing process for a one piece tank that involves three steps results in a consistently watertight and structurally stronger unit than previous tanks. The three steps comprise a process for producing the body of the tank, a process for producing a preliminary lid, and a process for producing the final tank. An important step in the process for producing the body of the tank is extending reinforcing steel (rebar) a distance above the concrete walls of the tank. After the preliminary lid is placed into a groove of the tank, the rebar is bent over the lid and a water stop is applied between the walls of the tank and the preliminary lid. The water stop can be any of several forms. In one form, the water stop is in the form of butyl or rubber strip which projects from the walls of the tank above the walls with the rebar. In an alternate form, the water stop is in the form of a gasket of plastic or other suitable material inserted in a groove at the top of the tank. Once the preliminary lid is in place and the rebar bent over the preliminary lid, reinforcing steel (rebar) is bent over the preliminary lid and secured to proper locations. Then concrete is poured to the top and above the sidewalls of the tank until completely full. The resulting cured structure is a one piece water tight tank with an integral water stop.

A fiber-reinforced component for use in a gas turbine engine includes a first braided fiber sleeve forming a cooling channel and a plurality of fiber plies enclosing the first braided fiber sleeve, with the plurality of fiber plies forming first and second walls separated by the first braided fiber sleeve. The fiber-reinforced component further includes a matrix material between fibers of the braided fiber sleeve and the plurality of fiber plies.