Provided is a material for molding, without a mold, a highly uniform structure comprising a resin and a non-resin such as metals and ceramic. The molding material provided by this invention is formed of a powder comprising a resin and at least one species of non-resin selected among metals and ceramic. The resin material has a uniformity index N below 0.2. N is determined by depositting the powder in a softened or melted state to form a structure in a temperature range between the resin material's minimum molding temperature and maximum molding tempeature+100 C.; measuring the structure's porosity Rn at 12 locations by image analysis; and dividing the variance of porosity Rn by the average porosity Rn. The minimum and maximum molding temperatures are the lowest and highest heater temperatures at which the resin material can be molded at a pressure of 3500 psi by injection molding, respectively.

A gas turbine engine component includes a structure including spaced apart first and second exterior walls that extend in a first direction to an endwall. The first and second exterior walls are joined at the endwall to provide a cooling cavity. A wishbone baffle is arranged in the cooling cavity and includes first and second interior walls respectively adjacent to the first and second exterior walls. The first and second interior walls extend in the first direction to and are joined by an apex to provide a first cavity. The wishbone baffle separates the first cavity from a second cavity provided between the apex and the endwall.

A gas turbine engine component includes a structure including spaced apart first and second exterior walls that extend in a first direction to an endwall. The first and second exterior walls are joined at the endwall to provide a cooling cavity. A wishbone baffle is arranged in the cooling cavity and includes first and second interior walls respectively adjacent to the first and second exterior walls. The first and second interior walls extend in the first direction to and are joined by an apex to provide a first cavity. The wishbone baffle separates the first cavity from a second cavity provided between the apex and the endwall.

Provided are a powder for laser manufacturing which can be stably manufactured and from which a three-dimensional manufactured object ensuring a manufacturing accuracy can be obtained and a using method thereof. A powder for ceramic manufacturing for obtaining a manufactured object by repeatedly sintering or fusing and solidifying in sequence a powder in an irradiation portion with laser light, in which the powder includes a plurality of constituent materials, at least one constituent material of the constituent materials is an absorber that relatively strongly absorbs the laser light compared to other constituent materials, and at least a part of the absorber changes to a different constituent material that relatively weakly absorbs the laser light by irradiation with the laser light and a using method of a powder in which the powder is used.

A resin composition for inorganic molded article production use, which is provided with inorganic particles each containing amorphous SiO.sub.2 and a photocurable resin composition, in which the photocurable resin composition contains a photocurable resin precursor and a photopolymerization initiator, the content of the inorganic particles is 60% by mass or more with respect to the total amount of the photocurable resin composition and the inorganic particles and is 60% by mass or more with respect to the entire amount of the resin composition for inorganic molded article production use, and the viscosity of the composition for inorganic molded article production use is 10000 mPa.Math.s or less.

A method of manufacturing a ceramic matrix composite (CMC) turbine nozzle shell is provided. The method includes: assembling a primary outer nozzle platform, a primary inner nozzle platform, a core and trailing edge preform, and an airfoil-shaped body; joining the primary outer nozzle platform to a secondary outer nozzle platform of the airfoil-shaped body; and joining the primary inner nozzle platform to a secondary inner nozzle platform of the airfoil-shaped body. Composite plies circumferentially surround the airfoil-shaped body, and their longitudinal edges are cut into fingers that are folded down. The fingers are interleaved between secondary platform plies to form the secondary outer and inner nozzle platforms.

A method of manufacturing a ceramic matrix composite (CMC) turbine nozzle shell is provided. The method includes: assembling a primary outer nozzle platform, a primary inner nozzle platform, a core and trailing edge preform, and an airfoil-shaped body; joining the primary outer nozzle platform to a secondary outer nozzle platform of the airfoil-shaped body; and joining the primary inner nozzle platform to a secondary inner nozzle platform of the airfoil-shaped body. Composite plies circumferentially surround the airfoil-shaped body, and their longitudinal edges are cut into fingers that are folded down. The fingers are interleaved between secondary platform plies to form the secondary outer and inner nozzle platforms.

A duct coupler assembly includes a female duct coupler, where the female duct coupler is coupled to a first duct segment. The female duct coupler includes a female duct coupler body having an inner surface having an inner diameter and a bayonet slot formed therein. The duct coupler assembly further includes a male duct coupler. The male duct coupler is coupled to a second duct segment. The male duct coupler includes a male duct coupler body having an outer surface having an outer diameter, where the outer diameter is smaller than the inner diameter of the inner surface of the female duct coupler body. The male duct coupler has a bayonet post extending from an outer surface of the male duct coupler body, and the male duct coupler body is positioned within the female duct coupler body such that the bayonet post is positioned within the bayonet slot wherein the male duct coupler is coupled with the female duct coupler.

A method for producing a gas sensor element (10), the gas sensor element including a diffusive porous layer (113) disposed in a measurement chamber (111) and exposed to the outside and a ceramic insulating layer (115) forming sidewalls of the measurement chamber. The method includes transferring green diffusive porous layer pieces (113x) cut in advance so as to have prescribed dimensions onto a first ceramic green sheet (110x); applying an insulating paste which later becomes the ceramic insulating layer to the first ceramic green sheet; laminating the first ceramic green sheet onto a second ceramic green sheet (120x) to form a ceramic laminate (200x); cutting the ceramic laminate along prescribed cutting lines C to obtain a plurality of gas sensor element pieces 10x; and firing the gas sensor element pieces.

A method for producing a gas sensor element (10), the gas sensor element including a diffusive porous layer (113) disposed in a measurement chamber (111) and exposed to the outside and a ceramic insulating layer (115) forming sidewalls of the measurement chamber. The method includes transferring green diffusive porous layer pieces (113x) cut in advance so as to have prescribed dimensions onto a first ceramic green sheet (110x); applying an insulating paste which later becomes the ceramic insulating layer to the first ceramic green sheet; laminating the first ceramic green sheet onto a second ceramic green sheet (120x) to form a ceramic laminate (200x); cutting the ceramic laminate along prescribed cutting lines C to obtain a plurality of gas sensor element pieces 10x; and firing the gas sensor element pieces.