Provided is a light activated rotor comprising typically a plurality of vanes affixed to a hub rotatable around the longitudinal axis of an axle. Each vane comprises a planar surface oriented generally perpendicular to the longitudinal axis of the axle with each vane separated into a first surface and a second surface. The first and second surface are adjacent and share a common boundary generally perpendicular to the longitudinal axis of the axle. Additionally, the first and second surfaces have differing emissivities. When the light activated rotor is illuminated with a radiant flux, the differing emissivities of the first and second surfaces produce a temperature gradient across the vane and generally perpendicular to the longitudinal axis, and a thermal creep force across the planar surface of the vane generates a revolution of the vane and the affixed hub around the longitudinal axis of the axle.

A method for assembling a set including an inner wall, a shrouded outer wall and an intermediate element, each presenting substantially circular sections, the shrouded outer wall presenting a shape substantially complementary to a shape of outer and inner surfaces of the intermediate element, and whose inner surface covers the outer surface of the intermediate element. In particular, the method includes a step of placing a brazing sheet, whose melting temperature is lower than melting temperatures of other elements of the set, over an assembly surface in contact with another assembly surface, and a step of heating, by a furnace, a set including the outer or inner walls and the intermediate element between which is interposed a brazing sheet so as to fix the outer or inner wall by brazing on the intermediate element.

The present invention relates to a fire resistant fan casing for a gas turbine engine. The casing has a projection such as a reinforcing rib or a mounting pad. The projection comprises at least one shell portion formed of a fiber/plastic composite material encasing a core of fire resistant material such as a metallic material or a ceramic matrix composite material.

A blade outer air seal support includes, at least one arc body having a first portion and a second portion, a blade outer air seal mounting region defined at least partially between the first portion and the second portion, and an interface feature interfacing the first portion and the second portion. The interface feature is configured such that axially aligned forces are communicated between the first and second portions through the interface feature, bypassing the blade outer air seal mounting region.

An additively manufactured thermally insulating structure comprising a base layer and a fire-resistant layer adjacent to the base layer that forms an air gap therebetween. A method for assembling a miniature gas turbine engine includes additively manufacturing an additively manufactured thermally insulating structure onto a static structure of the miniature gas turbine engine.

Provided are a coated member in which damage of a coating film can be suppressed in a high temperature environment and the coating may be performed at low cost, and a method of manufacturing the same. A coated member includes a bond coat and a top coat sequentially laminated on a substrate made of a Si-based ceramic or a SiC fiber-reinforced SiC matrix composite, wherein the top coat includes a layer composed of a mixed phase of a (Y.sub.1-aLn.sub.1a).sub.2Si.sub.2O.sub.7 solid solution (here, Ln.sub.1 is any one of Nd, Sm, Eu, and Gd) and Y.sub.2SiO.sub.5 or a (Y.sub.1-bLn.sub.1′b).sub.2SiO.sub.5 solid solution (here, Ln.sub.1′ is any one of Nd, Sm, Eu, and Gd), or a mixed phase of a (Y.sub.1-cLn.sub.2c).sub.2Si.sub.2O.sub.7 solid solution (here, Ln.sub.2 is any one of Sc, Yb, and Lu) and Y.sub.2SiO.sub.5 or a (Y.sub.1-dLn.sub.2′d).sub.2SiO.sub.5 solid solution (here, Ln.sub.2′ is any one of Sc, Yb, and Lu).

A turbine system including a sealing component is presented. The sealing component is positioned in a gap between adjacent turbine components of the turbine system. The sealing component includes a metallic shim including a high-temperature-resistant alloy in a single crystal form. A turbine shroud assembly including the sealing component is also presented.

A ring-shaped thermomechanical part for a turbine engine, comprising at least one coating including a polymeric matrix and fillers in non-deflagrating carbon exclusively comprising the chemical element C. A turbine engine comprising such a part.

Provided are a coated member in which damage of a coating film can be suppressed in a high temperature environment and the coating may be performed at low cost, and a method of manufacturing the same. A coated member includes a bond coat and a top coat sequentially laminated on a substrate made of a Si-based ceramic or a SiC fiber-reinforced SiC matrix composite, wherein the top coat includes a layer composed of a mixed phase of a (Y.sub.1-aLn.sub.1a) solid solution (here, Ln.sub.1 is any one of Nd, Sm, Eu, and Gd) and Y.sub.2SiO.sub.5 or a (Y.sub.1-bLn.sub.1′.sub.b).sub.2SiO.sub.5 solid solution (here, Ln.sub.1′ is any one of Nd, Sm, Eu, and Gd), or a mixed phase of a (Y.sub.1-cLn.sub.2c).sub.2Si.sub.2O.sub.7 solid solution (here, Ln.sub.2 is any one of Sc, Yb, and Lu) and Y.sub.2SiO.sub.5 or a (Y.sub.1-dLn.sub.2′.sub.d).sub.2SiO.sub.5 solid solution (here, Ln.sub.2′ is any one of Sc, Yb, and Lu).

A process of producing an article and an article made are provided. The process includes producing a near-net shape component. The process includes forming a consolidation shell by additive manufacturing. The consolidation shell defines an interior space having a geometry corresponding to a component. A metallic powder is provided to the interior space. Gas is removed from the interior space. The metallic powder is consolidated in the consolidation shell under sufficient heat and pressure to form the near-net shape component.