A silencer duct includes at least one element including a three-dimensional (3D) chamber having a portion that is at least one of non-vertical or non-linear. An acoustic absorbing member is self-supporting such that is may be positioned within the portion to substantially fill the portion, but does not sag or droop over time.

A method for manufacturing a ply is disclosed. The method includes printing the ply, the ply including a near net shape and a ceramic matrix composite nonwoven material. A ply is disclosed wherein the near net shape is a predetermined layer of an article. A method for manufacturing an article is also disclosed. The method includes printing a first ply and a second ply. The first ply includes a first near net shape and a first ceramic matrix composite nonwoven material, and the second ply includes a second near net shape and a second ceramic matrix composite nonwoven material. The method further includes applying the second ply to the first ply, and consolidating the first ply and the second ply.

A method of manufacturing of a structured cooling panel includes cutting of desized 2D ceramic into tissues; slurry infiltration in the tissues by at least one knife blade coating method; laminating the tissues in a multi-layer panel, with slurry impregnation after each layer, wherein the tissue has combined fibres and/or pre-build cooling holes; drying; de-moulding; sintering the multi-layer panel, wherein part of the combined fibres burns out during the sintering process leaving a negative architecture forming the cooling structure and/or the pre-build cooling holes define the cooling structure; finishing, using of i) post-machine, and/or ii) surface smoothening/rework, and/or iii) coating application, and/or other procedures.

A variable vane assembly for a gas turbine engine compressor and method of manufacturing same is described. A plurality of projections the inner and/or outer shroud which protruded into the annular gas path such as to ensure that a radial clearance gap, defined between the projections and a vane airfoil overhang portion, remains substantially constant throughout a substantial portion of the vane pivot arc of the variable vane. The method includes forming one cavities within the shroud, the cavities isolated from the annular gas path and disposed radially beneath at least each of the projections, and providing one or more structural reinforcing elements within the cavities.