A gas turbine engine article includes a silicon-containing ceramic wall that has an external combustion gaspath side and an internal side that borders a cooling air cavity. The external combustion gaspath side has an associated combustion gas flow direction there along. An array of cooling holes extends through the silicon-containing ceramic wall and connects the internal side with the external combustion gaspath side. The cooling holes are oriented to discharge cooling air to the external gaspath side in a direction counter to the combustion gas flow direction.

The present invention relates to a method for producing a component of a composite material comprising a metal matrix and incorporated intermetallic phases, which method comprises providing powders of at least one member of the group which comprises pure chemical elements, alloys, chemical compounds and material composites, the powder corresponding overall to the chemical composition which the composite material to be produced is intended to have, each individual powder being different to the chemical composition of the composite material to be produced, compacting the powders, bonding the powders to one another to form a unit and thermoplastically shaping the unit.

A composite bond coat may include a matrix and a reinforcing component. The matrix may be formed from silicon-based particles, and the reinforcing component includes silicon-based ceramic particles. The composite bond coat may be formed by introducing a precursor composition into a plume generated by a thermal spray gun to generate a thermal spray stream. The thermal spray stream may be directed at a major surface defined by a substrate of the component to form the composite bond coat. The precursor composition includes the matrix component and the reinforcing component.

Methods are provided for forming high temperature coating over ceramic components, such as ceramic turbomachine components. In various embodiments, the method includes the step or process of at least partially filling a reactor vessel with a reaction solution containing a solution-borne rare earth cation source. A silicon-containing surface region of a ceramic component is submerged in the reaction solution, and a solvothermal growth process is carried-out. During the solvothermal growth process, the reaction solution is subject to elevated temperature and pressure conditions within the reactor vessel in the presence of a silicate anion source, which reacts with the solution-borne rare earth cation source to grow a rare earth silicate layer over the silicon-containing surface region of the ceramic component.

A section of a gas turbine engine includes a ceramic component and a metallic component situated adjacent the ceramic component. The ceramic component and the metallic component are situated outside of a core flow path of the gas turbine engine. The section of a gas turbine engine also includes an interface between the ceramic component and a metallic component and a mullite-based coating disposed at the interface. The coating provides thermal protection to the ceramic component and the metallic component, and provides thermochemical protection against interaction between the ceramic component and the metallic component. A gas turbine engine and a method of protecting components in a gas turbine engine are also disclosed.

A ceramic component is generally provided that includes a silicon-based layer comprising a silicon-containing material (e.g., a silicon metal and/or a silicide) and about 0.001% to about 85% of an In-containing compound. For example, the silicon-based layer can be a bond coating directly on the surface of the substrate. Alternatively or additionally, the silicon-based layer can be an outer layer defining a surface of the substrate, with an environmental barrier coating on the surface of the substrate. Gas turbine engines are also generally provided that include such a ceramic component.

A method for forming a ceramic matrix composite article includes laying up a first group of plies; laying up a second group of plies, the first and second groups of plies being adjacent to each other; compacting the first group of plies and the second group of plies in the same processing step; and performing a first infiltration process on the first group of plies. The method also includes performing a second infiltration process on the second group of plies, the first infiltration process being one of a melt infiltration process or a chemical vapor infiltration process, and the second infiltration process being the other of the melt infiltration process or the chemical vapor infiltration process.

In some examples, an article may include a substrate and a coating on the substrate. In accordance with some of these examples, the coating may include a bond layer and an overlying layer comprising at least one oxide. In some examples, the bond layer comprises silicon metal and at least one of a transition metal carbide, a transition metal boride, or a transition metal nitride.

A turbomachine airfoil element has a substrate. The substrate defines an airfoil having a pressure side and a suction side. A plurality of fiber composite ribs are along the pressure side.

A section of a gas turbine engine includes a ceramic component and a metallic component situated adjacent the ceramic component. The ceramic component and the metallic component are situated outside of a core flow path of the gas turbine engine. The section of a gas turbine engine also includes an interface between the ceramic component and a metallic component and a mullite-based coating disposed at the interface. The coating provides thermal protection to the ceramic component and the metallic component, and provides thermochemical protection against interaction between the ceramic component and the metallic component. A gas turbine engine and a method of protecting components in a gas turbine engine are also disclosed.