An article is disclosed including a manifold, an article wall having at least one external aperture, and a post-impingement cavity disposed between the manifold and the article wall. The manifold includes an impingement plate defining a plenum having a plenum surface, and at least one impingement aperture. The at least one impingement aperture interfaces with the plenum at an intake aperture having a flow modification structure, which, together with the at least one impingement aperture, defines an exhaust aperture. The manifold exhausts a fluid from the plenum into the intake aperture, through the at least one impingement aperture, out the exhaust aperture, into the post-impingement cavity, and through the at least one external aperture.

An article is disclosed including a manifold, an article wall having at least one external aperture, and a post-impingement cavity disposed between the manifold and the article wall. The manifold includes an impingement plate defining a plenum having a plenum surface, and at least one impingement aperture. The at least one impingement aperture interfaces with the plenum at an intake aperture having a flow modification structure, which, together with the at least one impingement aperture, defines an exhaust aperture. The manifold exhausts a fluid from the plenum into the intake aperture, through the at least one impingement aperture, out the exhaust aperture, into the post-impingement cavity, and through the at least one external aperture.

A self-sealing impingement cooling tube comprises a perimeter wall (51) defining a first end (54) and a second end (53), for example these may be a trailing edge and leading edge ends of an aerofoil. First and second wall sections extend from the first end (54) to the second end, the first and second wall sections joining at the first end. An adjustable gap (53) resides between the wall sections at the second end. One or both of the first and second wall sections is resiliently deformable such that the first and second wall sections can be positioned closer together and the adjustable gap (53) simultaneously reduced whereby to enable the tube to be inserted into a cavity which has a dimension smaller than the distance between the first and second wall sections when the perimeter wall (51) is not under load.

Turbine nozzles are provided for gas turbine engines. The turbine nozzle includes an arcuate inner band; an arcuate outer band; and a nozzle vane disposed between the arcuate inner band and the arcuate outer band. The radially inner end of the nozzle vane is attached to the arcuate inner band through an interlocking transition zone comprising a plurality of projections alternately extending from the radially inner end of the nozzle vane and the arcuate inner band, respectively, to undetachably couple the nozzle vane and the arcuate inner band. Optionally, the radially outer end of each nozzle vane is also attached to the arcuate outer band through an interlocking transition zone.

An apparatus is provided for a turbine engine. This turbine engine apparatus includes an annular nozzle. The annular nozzle includes an inner monolithic body and an outer monolithic body. The inner monolithic body includes an inner shroud and a plurality of vanes. The inner shroud extends axially along and circumferentially around an axis. The vanes are arranged circumferentially about the axis in an array. Each of the vanes projects radially out from the inner shroud to a respective outer distal end. The outer monolithic body is radially outboard of and circumscribes the inner monolithic body. The outer monolithic body is configured as or otherwise includes an outer shroud. The outer shroud extends axially along and circumferentially around the axis. The outer shroud radially engages each of the vanes at the respective outer distal end.

An article is disclosed including a manifold, an article wall having at least one external aperture, and a post-impingement cavity disposed between the manifold and the article wall. The manifold includes an impingement plate defining a plenum having a plenum surface, and at least one impingement aperture. The at least one impingement aperture interfaces with the plenum at an intake aperture having a flow modification structure, which, together with the at least one impingement aperture, defines an exhaust aperture. The manifold exhausts a fluid from the plenum into the intake aperture, through the at least one impingement aperture, out the exhaust aperture, into the post-impingement cavity, and through the at least one external aperture.

A multilayer acoustic treatment panel including a first cellular-structure core sandwiched between a perforated skin and an intermediate skin; and a second cellular-structure core sandwiched between the intermediate skin and a continuous skin. The perforated skin includes at least one pair of high-porosity zones presenting a perforation ratio greater than a perforation ratio of a remainder of the perforated skin and including an inlet zone and an outlet zone longitudinally spaced apart from each other, the high-porosity zones of a given pair communicating through the first cellular-structure core and the intermediate skin with the two ends of a soundwave flow channel arranged in the second cellular-structure core.

A nozzle sector for a sectorized annular stator of a gas turbine, comprising an inner platform and an outer platform, said inner platform and said outer platform being substantially concentric with respect to turbine rotational axis and spaced apart from each other by at least an airfoils, wherein each one of said inner platform and said outer platform has a platform leading edge, a platform trailing edge and a first and a second platform sidewall edge, each one of said sidewall edges being extending from said platform leading edge to said platform trailing edge of the respective platform, wherein each one of said first and said second sidewall edges has a leading portion, a trailing portion, and an intermediate portion comprised between said leading portion and said trailing portion.

A nozzle sector for a sectorized annular stator of a gas turbine, comprising an inner platform and an outer platform, said inner platform and said outer platform being substantially concentric with respect to turbine rotational axis and spaced apart from each other by at least an airfoils, wherein each one of said inner platform and said outer platform has a platform leading edge, a platform trailing edge and a first and a second platform sidewall edge, each one of said sidewall edges being extending from said platform leading edge to said platform trailing edge of the respective platform, wherein each one of said first and said second sidewall edges has a leading portion, a trailing portion, and an intermediate portion comprised between said leading portion and said trailing portion.