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.

A seal mechanism (20A) is disposed on an outer circumferential side of a rotor (2) extending along an axis (O) to perform sealing between the seal mechanism and the outer circumferential surface (2a) of the rotor (2). The seal mechanism (20A) includes a main body portion (21A) having a cylindrical shape, and into which the rotor (2) is inserted; and a plurality of hole portions (22) formed on an inner circumferential surface of the main body portion (21A) to face an outer circumferential surface of the rotor (2). The hole portions (22) are within a range in which a hole depth h is equal to or smaller than a hole diameter d.

A profiled element used is disclosed for generating a force, the profiled element comprising a material having an active surface; a plurality of cavities located on the active surface of the material, the plurality of cavities comprising pin holes, each pin hole having an opening of a micrometric size on the active surface and a depth of a micrometric size greater than its diameter; wherein each pin hole is hermetically sealed on the opposite side of the cavity; and further wherein an airflow circulation against the active surface of the material causes a pressure change on the active surface and inside each of the plurality of cavities thereby generating a force.

A thermally responsive flow meter may comprise a coil and a plate coupled to the coil. The plate may define a first airflow aperture. The plate may translate in a circumferential direction in response to a thermal expansion of the coil. The thermally responsive flow meter may regulate the flow of air through a second airflow aperture.

An air intake of a turbojet engine nacelle includes an annular structure including an outer fairing defining an aerodynamic outer surface and an inner fairing defining an aerodynamic inner surface. The outer and inner fairings are connected upstream by an air intake lip forming a leading edge. The inner fairing includes an outer skin fixed to the air intake lip by an upstream fixation flange, and the outer skin is configured to be fixed to an outer fan casing by a downstream fixation flange. The air intake includes at least one independent acoustic panel attached to the outer skin and which includes a perforated acoustic skin and a cellular core.

Aircraft fuel ice capturing filter device housings, aircraft fuel ice capturing filter devices, and methods of use are provided.

Aircraft fuel ice capturing filter device housings, aircraft fuel ice capturing filter devices, and methods of use are provided.

Acoustic treatments for components of gas turbine engines are described. The acoustic treatments include an acoustic resonator having a backing chamber defining a respective volume and a neck arranged relative to the backing chamber and defining an opening, wherein the neck has a length and a cross-sectional area. The acoustic resonator cell satisfies the following relationships: (1) l/L=0.2-0.8, where l is a length of the neck and L is a depth of the backing chamber and (2) a/A=0.02-0.20, where a is a cross-sectional area of the neck and A is a cross-sectional area of the backing chamber.

A fan section for a gas turbine engine according to an example of the present disclosure includes, among other things, a fan rotor having fan blades, and a plurality of fan exit guide vanes positioned downstream of the fan rotor. The fan rotor is configured to be driven through a gear reduction. A ratio of a number of fan exit guide vanes to a number of fan blades is defined. The fan exit guide vanes are provided with optimized sweep and optimized lean.

A turbine section of a turbomachine includes a housing that houses and supports the rotating group for rotation about an axis. The housing defines a circumferential inlet passage that extends about the axis. The housing defines a turbine wheel upstream area that is disposed downstream of the circumferential inlet passage and upstream of the turbine wheel. The housing defines an outlet that is downstream of the turbine wheel. Furthermore, the turbine section includes a first flow path that extends from the circumferential inlet passage, through the turbine wheel upstream area, across the turbine wheel, to the outlet. Moreover, the turbine section includes a recirculation flow path that extends from the circumferential inlet passage, through the turbine wheel upstream area, and back to the circumferential inlet passage.