A method includes forming a ceramic matrix composite component by infiltrating an array of ceramic-based fibers with a ceramic-based matrix; forming a plurality of cooling holes in the ceramic matrix composite component; applying a slurry of particles in a carrier fluid to the ceramic matrix composite component such that the slurry passes through the cooling holes and wicks into the ceramic matrix composite material; and processing the ceramic matrix composite component to remove the carrier fluid, thereby leaving a filler at a wall surface of the plurality of cooling holes. A component is also disclosed.

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 rotor for a machine under this disclosure could be said to include a hub having a plurality of blades extending radially outwardly of the hub. At least one of the hub and the plurality of blades is formed of at least two metal materials. The two metal materials are selected to have different thermal expansion coefficients such that the overall rotor will be more resistant to forces it may experience as temperature or speed increases. There are layers of each of the two metal materials, with an intermediate gradient wherein the two materials are mixed. Alternatively, a shape memory alloy may be used. A method is also disclosed.

An article has a metallic substrate having a plurality of recesses. A first coating is at least at the recesses and has: a splatted layer; and a columnar layer atop the splatted layer. A second coating is away from the recesses and has: a columnar layer atop the substrate without an intervening splatted layer.

A transition exit frame (10) for supporting a transition (12) extending downstream from a combustor (14) to a turbine assembly (16) in a turbine engine (18) and including one or more transition exit frame inserts (20) configured to reduce thermal distortion created during operation of the turbine engine (18) is disclosed. The transition exit frame (10) may be formed from one or more transition exit frame bodies (22). The transition exit frame body (22) may be formed from a first material (24) having a first coefficient of thermal expansion. The transition exit frame insert (20) may form at least a portion of the transition exit frame body (22). The transition exit frame insert (20) may be formed from a second material (26) having a second coefficient of thermal expansion that is different than the first coefficient of thermal expansion of the first material (24) to reduce distortion within the transition exit frame body (22) during operation of the turbine engine (18).

A turbine vane assembly for use in a gas turbine engine includes an endwall, a flow path component, and a load-distribution system. The endwall is arranged around a central axis of the turbine vane assembly. The flow path component is configured to direct fluid flow through the turbine vane assembly. The load-distribution system is positioned between the endwall and the flow path component to distribute loads transmitted between the endwall and the flow path component.

A shroud hanger assembly or shroud assembly is provided for dimensionally incompatible components wherein the assembly includes a multi-piece hanger, for example having a forward hanger portion and a rearward hanger portion. A cavity is formed between the parts; wherein a shroud may be positioned which is formed of a low coefficient of thermal expansion material. The hanger and shroud may be formed of the same material or differing materials in order to better match the thermal growth between the hanger and the shroud. When the shroud is positioned within the hanger opening or cavity, one of the forward and rearward hanger portions may be press fit or otherwise connected into the other of the forward and rearward hanger portion.

Each fuel injector has a main nozzle and pilot nozzle. A main fuel manifold to supply fuel to the main nozzle of each fuel injector and pilot fuel manifold to supply fuel to the pilot nozzle of each fuel injector. The main fuel manifold includes plurality of flexible main fuel pipes. Also, plurality of cross-piece connectors including a stem and four arms. The stem of each connector mounted on one fuel injector. The first and third arms extend in opposite directions from the stem and second and fourth arms extend in opposite directions from the stem. Each fuel pipe interconnects the first arm of one connector with a third arm of an adjacent connector and each connector so the first and third arms are at an angle relative perpendicular to the axis of the annular combustion chamber casing so the main fuel manifold extends around the combustion chamber casing sinusoidally.

An object is to provide a variable-geometry exhaust turbocharger including a variable nozzle mechanism in which nozzle supports may not deform under a high-temperature condition. A variable-geometry exhaust turbocharger (1) includes: a nozzle mount (2); a nozzle support (6) having a first end coupled to a first face (2a) of the nozzle mount; a nozzle plate (4) coupled to the second end of the nozzle support and supported to be separated from the first face (2aa) of the nozzle mount, the nozzle plate having a first face (4a) coupled to the nozzle support and a second face (4b) which is opposite to the first face and which faces an exhaust gas channel (20) through which exhaust gas flows: a plurality of nozzle vanes (8) rotatably supported between the nozzle mount and the nozzle plate; and a variable nozzle mechanism (10) configured to change vane angles of the nozzle vanes to control a flow of the exhaust gas flowing between the nozzle mount and the nozzle plate. The nozzle plate is formed of a material having a smaller linear expansion coefficient than that of a material forming the nozzle mount.

An airfoil assembly includes a support carrier and an airfoil unit that includes a platform, an airfoil, and a mount. The platform defines a boundary of a gas path of the airfoil assembly. The airfoil extends away from platform and the mount extends away from the platform opposite the airfoil. The support carrier is coupled with the airfoil unit and engages the mount.