An acoustic absorber for a gas turbine engine includes a back sheet, a face sheet spaced apart from the back sheet and defining a plurality of perforations, and a core layer positioned between the back sheet and the face sheet and comprising a plurality of cells. The core layer comprises an outer wall extending between the back sheet and the face sheet to define an outer boundary of at least one cell of the plurality of cells and an inner wall positioned within the outer boundary to divide the at least one cell of the plurality of cells into an outer damping volume and an inner damping volume, the inner damping volume being at least partially surrounded by the outer damping volume.

A panel for attenuating noise is disclosed comprising a face skin having a first inner surface, a base skin having a second inner surface, a cellular core connected to and forming a plurality of cells between the face skin and the base skin, wherein the cellular core is defined by a cell structure having a plurality of cell walls extending between the face skin and the base skin defining each of the plurality of cells and a septum disposed within each of the plurality of cells, the septum defining an upper chamber proximate the face skin and a lower chamber proximate the base skin, wherein the face skin comprises a plurality of perforations fully through the face skin and in fluid communication with the upper chamber.

An acoustic absorption cell including a bottom wall extending in a plane orthogonal to an axial direction, an enclosure including a first axial end secured to the bottom wall, and an acoustic horn extending inside the enclosure between a first opening of the horn and a second opening of the horn smaller than the first opening, the horn being secured to a second axial end of the enclosure opposite the first axial end, and the first and second openings of the horn each extending in a plane orthogonal to the axial direction. The horn includes at least one retaining arm protruding from the horn inside the enclosure and fixed to the bottom wall or to the enclosure.

A tubular ventilation sleeve for a turbomachine distributor, in particular for an aircraft, the sleeve having a generally elongate shape along an axis (A-A) and including a perforated tubular wall around said axis, one of the axial ends of the sleeve being open and the other being closed by a bottom wall, wherein it further includes support beams when the sleeve is made by additive manufacturing, the beams extending inside the sleeve between the tubular wall and the bottom wall and having a longitudinal cross-section with a generally triangular shape, two sides of which are respectively connected to the tubular wall and the bottom wall and the last side of which is free and extends inside the sleeve, perforations in the tubular wall being provided between the support beams.

An impeller includes a body with an interior channel extending through the body along a centerline axis of the impeller. A plurality of blades is connected to the body on a forward end of the impeller centerline axis. The plurality of blades surrounds the interior channel and is fluidly connected to an array of inlets. An array of pentagonal channels extends through the body and radially outward in a spiral pattern. Each pentagonal channel is fluidly connected to a corresponding vane inlet and a corresponding pentagonal-shaped outlet. Each channel maintains a pentagonal cross-section shape from the inlet to the outlet. Each downward-sloping face of the cross section is more than 35 degrees from a horizontal plane perpendicular to the centerline axis of the impeller.

An aircraft turbine engine module, including a degassing tube and an ejection cone. The tube and the cone are engageable together by structures which cause them to be centered when engaged together. Also provided is a locating and adjusting tool for assembling the module.

The invention provides a gas turbine combustor having structural reliability against vibration of fuel nozzles caused by fluid force and high environmental performance by uniform combustion in a combustion chamber. The gas turbine combustor comprises a fuel nozzle configured to inject fuel, and a fuel nozzle plate including a hole section into which an insertion section located in a root part of the fuel nozzle is inserted. The fuel nozzle includes a male screw section at least on an outer circumferential surface of a downstream portion viewed from a flowing direction of the fuel in the insertion section. The fuel nozzle plate includes a female screw section in the hole section. The female screw section screws with the male screw section. The fuel nozzle includes the insertion section. An upstream end portion of the insertion section is metallurgically joined to an upstream end portion of the fuel nozzle plate.

Methods and apparatus for gas turbine frame flow path hardware cooling are disclosed. An example engine fan case includes an outer band and an inner band, the outer band and the inner band connected using a double-walled vane, the vane including openings to pass cooling air flow from the outer band to an airfoil of the fairing, and an end segment seal, the seal formed on an edge of the fairing using an auxetic material.

A method of controlling an extent of a thermal barrier coating (TBC) sheet spall and a hot gas path (HGP) component are disclosed. The method provides an HGP component having a body with an exterior surface. Controlling the extent of the TBC sheet spall includes forming a TBC over a selected portion of the exterior surface of the body. The TBC includes a plurality of segments in a cellular pattern. Each segment is defined by one or more slots in the TBC, and each segment has a predefined area such that the extent of the TBC sheet spall is limited by the predefined area of each of the plurality of segments that constitute the TBC sheet spall.

An apparatus and method relating to a cooling hole of a component of a turbine engine. The component can include a wall separating the hot gas fluid flow from the cooling fluid flow and having a heated surface along which the hot gas fluid flow flows and a cooled surface facing the cooling fluid flow and at least one cooling hole comprising at least one inlet at the cooled surface, at least one outlet at the heated surface, with the outlet having a modified outlet shape.