A method for improving thermal efficiency of a heating device that reduces an amount of heat flowing out from a heating device 11 to the outside by installing a heat-resistant inorganic conjugated molded product 16 in and along a pathway 15 for heated gas generated from the heating device 11 without interrupting the flow of heated gas passing the pathway 15, heating the inorganic conjugated molded product 16 with the heated gas, and putting radiation heat from the heated inorganic conjugated molded product 16 back into the heating device 11, the inorganic conjugated molded product 16 being provided with an interior layer and an exterior layer, the exterior layer consisting of a coverture for inorganic materials that protects the interior layer from heated gas.

A process of producing a ceramic matrix composite component. The process includes positioning a plurality of ceramic matrix composite plies on top of one another and forming a cavity therein. At least a portion of the cavity includes a terminal diameter sufficiently small to permit infiltration of a densifying material. The plurality of ceramic matrix composite plies are densified to form a densified body. The densifying results in the portion of the cavity including the terminal diameter being filled with densifying material and the cavity is present in the densified body. A ceramic matrix composite having cavities therein is also disclosed.

A turbine vane for a gas turbine engine incorporating a ceramic matrix composite airfoil is disclosed in this paper. The turbine vane includes an attachment unit configured to mount the ceramic matrix composite airfoil to other metallic components of the turbine vane.

There is provided a component formed from a plurality of laminates stacked on one another, thereby defining a stacked laminate structure having a leading edge and a trailing edge. Each of the plurality of laminates is formed from a ceramic matrix composite material. In addition, a plurality of interior cooling channels are defined within an interior of the stacked laminate structure and extend longitudinally between the leading edge and the trailing edge. A metal support structure is arranged so as to extend through first openings in the laminates and through the stacked laminate structure.

The disclosure describes a gas turbine engine blade that includes a dovetail portion comprising a first ceramic matrix composite, an airfoil portion comprising the first ceramic matrix composite, a transition portion between the airfoil portion and the dovetail portion, and a platform portion that substantially surrounds the transition portion. The airfoil portion may define a capture feature that is configured to engage with and mechanically restrain the platform portion from moving beyond the capture feature toward a tip of the airfoil portion.

A container comprising: a container body that includes a wall portion separating inside and outside and is formed of a long-fiber-reinforced silicon-carbide composite material obtained by combining monofilaments of silicon carbide with a silicon carbide matrix, the wall portion having a thickness equal to a specific dimension; and a lid configured to close an opening of the container body, formed of a material containing at least silicon carbide, and equipped with such a wall portion separating inside and outside that thickness is within a range of 1 to 3 times the specific dimension.

A gas turbine engine may comprise a blade track and a method of making the same. The blade track may be constructed of ceramic matrix composite components including segments and joints.

The present approach relates to the fabrication of a composite material via a multi-step heating process. In one heating stage an internal region of a preform is heated by application of electro-magnetic radiation. In another heating stage, a region near the surface of the preform is heated from the exterior inward.

The present disclosure provides a method of manufacturing a composite sandwich panel having a core formed of a plurality of cells extending vertically between a first skin and a second skin. The method includes creating at least one first strip and a second strip from a temporary material, each strip having at least one cavity having a succession of aligned half-cells, lining the cavity of the first strip with a fibrous ply, assembling the first strip and the second strip by interlocking the cavity of the first strip with the cavity of the second strip and trapping the fibrous ply therebetween, and trimming excess temporary material of the entirety of the strips formed during the preceding assembly step so as to form a new cavity which forms a succession of aligned half-cells.

A ceramic matrix composite article includes a chemical vapor infiltration ceramic matrix composite base portion including ceramic fiber reinforcement material in a ceramic matrix material having between 0% and 5% free silicon. The ceramic matrix composite article further includes a melt infiltration ceramic matrix composite covering portion including a ceramic fiber reinforcement material in a ceramic matrix material having a greater percentage of free silicon than the chemical vapor infiltration ceramic matrix composite base portion.