An apparatus and method for flowing cooling air through an outer wall of an engine component such as an airfoil. The airfoil having the outer wall can include a skin layer and a porous layer. The skin layer can include a skin cooling circuit for providing the cooling air from an interior of the airfoil to the exterior of the airfoil through the porous layer.

A platform seal and damper assembly for turbomachinery (100), such as fluidized catalytic cracking (FCC) expanders or gas turbine engines; and methodologies for forming such assembly are provided. An axially-extending groove (160) is arranged on a side (162) of a respective platform. Groove (160) is defined by a radially-outward surface (168) at an underside of the platform and a surface (170) extending with a tangential component (T) toward radially-outward surface (168). A seal and damper member (152) is disposed in groove (160), where the body of seal and damper member has adjoining surfaces (190, 188) configured to respectively engage, in response to a camming action, with the surfaces (168, 170) that define the axially-extending groove. The camming action being effective to produce an interference fit of the seal and damper member (152) with the side of the respective platform (162) and an opposed side (163) of an adjacent platform.

Disclosed is a method for producing a blade for a turbomachine, in particular for an aero engine. The method comprises providing at least one blade airfoil with a first platform region and at least one blade root with a second platform region and joining the blade airfoil and the blade root at the respective platform regions by a friction welding method at a common joint region of the platform regions, the blade airfoil and the blade root being made of materials which are different from each other. Also disclosed is a blade which is and/or can be obtained by such a method.

A shroud for a compressor is provided. The shroud may include a first annular portion constructed of a first material, a second annular portion coupled to the first annular portion and constructed of a second material, and a first coating disposed on the first annular portion and constructed of a third material. At least one of the first material, the second material, and the third material may be a different material from at least one other of the first material, the second material, and the third material.

Applying material along parallel welding lines per welding layer, and by changing direction of extension of the welding tracks by 90° for the next welding layer, provided.

A blade outer airseal has a body comprising: an inner diameter (ID) surface; an outer diameter (OD) surface; a leading end; and a trailing end. The airseal body has a metallic substrate and a coating system atop the substrate along at least a portion of the inner diameter surface. At least over a first area of the inner diameter surface, the coating system comprises an abradable layer system comprising a plurality of layers including a relatively erosion-resistant first layer atop a relatively abradable second layer.

An airfoil and a method of manufacturing an airfoil may be provided, where the airfoil comprises a core and a shell. The core comprises core ceramic fibers extending along a span of the airfoil. The shell surrounds the core and includes shell ceramic fibers. Substantially all of the core ceramic fibers are arranged in a radial direction. The airfoil may also be a ceramic matrix composite formed by infiltrating the core and the shell with a matrix material.

Methods for performing in situ balancing of an internal rotating component of a gas turbine engine are provided. The method can include inserting a repair tool through an access port of the gas turbine engine with the repair tool including a tip end positioned within the gas turbine engine and a material supply end positioned outside the gas turbine engine. The tip end of the repair tool is positioned adjacent to a surface of the internal rotating component of the gas turbine engine. A new material is supplied from the material supply end of the repair tool to the tip end of the repair tool; and is expelling from the tip end of the repair tool in a direction of the surface of the rotating component such that the new material is added onto a portion of the rotating part.

The subject matter of this specification can be embodied in, among other things, a fuel delivery component, a substantially rigid, unitary structure formed as a single piece of material, and at least a first seamless lumen defined by the unitary structure as a first loop.

Systems and methods are disclosed for anti-rotation lugs. A stator for a gas turbine engine may comprise an outer shroud, an inner shroud, and a plurality of vanes located between the outer shroud and the inner shroud. A plurality of anti-rotation lugs may be coupled to the inner shroud. The anti-rotation lugs may be configured to contact a diffuser case in order to prevent rotation of the stator. The anti-rotation lugs may comprise a body and a tapered shoulder. The tapered shoulder may distribute stress concentrations in the anti-rotation lugs.