A system and method for bonding together a facesheet and an acoustic screen of an acoustic liner using a solid adhesive film having a first adhesive side opposite a second adhesive side are provided. The system includes a solid adhesive film having a first adhesive side opposite a second adhesive side; an acoustic screen bonded to the first adhesive side of the solid adhesive film; and a facesheet bonded to the second adhesive side of the solid adhesive film. The method includes bonding the facesheet to the first adhesive side of the solid adhesive film and bonding the acoustic screen to the second adhesive side of the solid adhesive film.

An acoustic panel for an aircraft nacelle air intake comprising a resistive skin perforated by noise absorption holes and a core against which the resistive skin extends, wherein the resistive skin has a smooth visible face and a castellated rear face with alternating ribs and grooves. The noise absorption holes are formed exclusively in the grooves, i.e., in a zone where the skin is less thick, which enables the holes to have a diameter that is both greater than the thickness of the skin and small enough not to have any impact on drag. The mechanical strength of the resistive skin provided by the ribs ensures that the lesser thickness of the resistive skin in the grooves does not render the resistive skin overly flexible.

An angular sector of a fixed blade ring of a turbomachine, in particular a stator or a guide vane assembly, includes, relative to the axis of said fixed blade ring, a radially outer platform, a radially inner platform, at least two blades extending between said platforms, and at least one block of abradable honeycomb material extending on the inside of the inner platform between transverse ends of the sector. The block of abradable material includes at least one transverse end wall shaped according to a toothed profile having at least one radially oriented tooth extending across an entire radial thickness of said block.

Systems and methods are disclosed herein for passively managing cooling air in a gas turbine engine. A cooling air supply line may supply cooling air to a component in the gas turbine engine. A metering coupon may have a negative coefficient of thermal expansion. The metering coupon may allow more airflow through the metering coupon and through the component in response to an increase in temperature.

A composite layer system is presented. The composite layer system includes a metallic substrate, a structured surface, and a thermal protection system. The structured surface may be additively manufactured onto the metallic substrate and includes structured surface features formed to project above the metallic substrate. Each of the structured surface features are separated from adjacent structured surface features by grooves. The thermal protection coating may be thermally sprayed onto the structured surface and is bonded to each of the structured surface features.

Aspects of the disclosure regard a fan case assembly for a gas turbine engine, the fan case assembly comprising a fan case having an inner surface, a fan track liner comprising abradable material layer, and a rear acoustic panel arranged aft of the fan track liner. The fan track liner and the rear acoustic panel are integrated into a single panel structure attached to the fan case inner surface.

A gas turbine engine includes a fan case assembly adapted to extend around blades of a fan rotor included in the gas turbine engine. The fan case assembly includes an annular case that extends around an axis, an acoustic panel coupled to the annular case and configured to dampen vibrations and a bolting arrangement that couples the acoustic panel to the annular case.

A turbomachinery stator apparatus includes: a compressor casing including a casing wall defining an arcuate flowpath surface and an opposed backside surface, the flowpath surface defining at least two spaced-apart rotor lands; and a stator vane row of stator vanes disposed inside the compressor casing; wherein the casing wall includes at least one hollow structure; and wherein the casing wall is a single monolithic whole, wherein the stator vanes are integrally formed as part of the monolithic whole.

A method for manufacturing a sound absorption structure comprising a cellular panel, a porous layer positioned on a cellular panel first face, a reflective layer positioned on a cellular panel second face and a plurality of acoustic elements positioned in the cellular panel. The method comprises the steps of producing, for each acoustic element, a recess in the cellular panel opening out onto the first and second faces of the cellular panel, inserting the acoustic elements into their recesses, laying an anchoring layer on the second cellular panel face, curing or polymerization at a first pressure to connect each acoustic element to the cellular panel and/or to the anchoring layer, putting in place the porous layer and the reflective layer, and curing or polymerization at a second pressure to connect the porous layer and the reflective layer to the cellular panel.

The present disclosure provides a co-bonded acoustic liner, including a honeycomb core with cells therein, a thermoset-based plastic septa material co-bonded to a top face of the honeycomb core; a facesheet with perforations to enable airflow, co-bonded to the thermoset-based plastic septa material; and an optional backside skin positioned under the honeycomb core, co-bonded to the bottom face of the honeycomb core, wherein the liner supports a single degree of freedom acoustic structure. The disclosure further provides methods of preparing and using such co-bonded acoustic liners.