An airfoil includes an airfoil section that has an airfoil wall that defines a leading end, a trailing end, and first and second sides that join the leading end and the trailing end. The first and second sides span in a longitudinal direction between first and second ends, and the airfoil wall circumscribes an internal core cavity. An arced rib extends from the first side to the second side and divides the internal core cavity into a forward cavity and an aft cavity. A cooling passage network is embedded in the airfoil wall aft of the rib and between inner and outer portions of the airfoil wall. The network includes a cooling passage leading edge and a cooling passage trailing edge. The aft core cavity has a central cavity section and a cavity lobe. The cavity lobe projects between the rib and the cooling passage leading edge.

Methods for creating a cast component, along with the resulting cast components, are provided. The method may include heating a mold having a cavity therein; supplying a first molten metal material into the cavity of the mold such that the first molten metal material is directed to a first portion of the cavity of the mold; supplying a second molten metal material into the cavity of the mold such that the second molten metal material is directed to a second portion of the cavity of the mold, wherein the first molten metal material is compositionally different than the second molten metal material; and thereafter, allowing the first molten metal material and the second molten metal material to form the cast component.

A method of forming a ceramic matrix composite component. The ceramic matrix composite component is adapted for use in a gas turbine engine. The method including forming the component using ceramic materials and infiltrating the component with a matrix material.

Cast components are provided that include a first section comprising a first metal material and having first grains with a first average grain size and a second section comprising a second metal material and having second grains with a second average grain size.

An inner coating layer for solid-propellant rocket engines, constituted by a material comprising from 45% to 55% wt. of a a cross-linkable, unsaturated-chain polymer base, from 11% to 13% wt. of silica, from 15% to 25% wt. of vulcanizing agents and plasticizers, from 5% to 7% wt. of aramid fiber and from 10% to 15% wt. of microspheres made of a material selected among glass, quartz and nano clay, having diameter lower than 200 μm, density comprised between 0.30 and 0.34 g/cc and resistance to hydrostatic pressure greater than, or equal to, 4500 psi.

A coated substrate has a substrate and a coating system having one or more ceramic layers. At least a first layer of one of the one or more ceramic layers is a columnar layer having as-deposited columns and intercolumn gaps. The intercolumn gaps have a mean width at least one of: at least 4.0 micrometers; and at least 1.5% of a thickness of said first layer.

During a material removal method, a component is received that includes a component body and a coating on the component body. The component body includes metallic first material. The coating includes second material that is different from the first material. A solution is received that includes nitric acid and hydrogen peroxide. At least a portion of the coating is subjected to the solution in order to remove at least some of the second material from the component.

A method for providing micro-channels in a hot gas path component includes forming a first micro-channel in an exterior surface of a substrate of the hot gas path component. A second micro-channel is formed in the exterior surface of the hot gas path component such that it is separated from the first micro-channel by a surface gap having a first width. The method also includes disposing a braze sheet onto the exterior surface of the hot gas path component such that the braze sheet covers at least of portion of the first and second micro-channels, and heating the braze sheet to bond it to at least a portion of the exterior surface of the hot gas path component.

An airfoil includes an airfoil section that has an airfoil wall that defines an arced leading end, a trailing end, and first and second sides that join the arced leading end and the trailing end. The first and second sides span in a longitudinal direction between first and second ends. The airfoil wall circumscribes an internal core cavity. There is an arced rib in the internal core cavity. A cooling passage network is embedded in the airfoil wall between inner and outer portions of the airfoil wall. The cooling passage network has a trailing edge and an arced leading edge.

A nanocellular single crystal nickel based material is provided having a thermal diffusivity in the range of 0.0002 cm{circumflex over ( )}2/s to 0.02 cm{circumflex over ( )}2/s and a thermal conductivity in the range of 0.024 W/mK to 9.4 W/mK. The nanocellular single crystal nickel based material may be used to form turbine engine components. The nanocellular single crystal nickel based material may be produced by providing a first solution containing a nickel precursor and deionized water, providing a second solution containing a structure controlling polymer/surfactant and an alcohol, mixing the first and second solutions into a solution containing a reducing agent to form a third solution, and processing the third solution to create the nanocellular single crystal based material.