A gas turbine engine assembly adapted to separate a high pressure zone from a low pressure zone includes a pressure-activated seal. The pressure-activated seal is arranged in a channel formed between a first component and a second component that opens toward the high pressure zone.

A method is provided for forming a structural panel. During this method, a core structure is formed by shaping a first portion of a sheet of ribbon material to form a first baffle and a first septum. Thermoplastic material is then overmolded onto the ribbon material, between the first baffle and the first septum, to form a first set of walls.

The present disclosure relates to a cell structure for an acoustic attenuation device for a nacelle of an aircraft propulsion assembly. This cell structure includes lateral partitions forming channels that each extend between a first end and a second end and skin elements arranged so that each channel is at least partly closed at the first end thereof by at least one skin element. Each skin element is connected to a respective lateral partition and can move relative to the other lateral partitions. A continuous skin can be assembled on this cell structure so as to at least partly close the channels at the second end thereof and to thus form an acoustic attenuation device.

A guide vane ring for a turbomachine minimizes a leakage flow that passes through a recess into which a guide vane disk is inserted. It has a guide vane row having a plurality of guide vanes, each having a vane airfoil and a vane disk, as well as an inner ring having an inner ring surface facing the plurality of guide vanes. Viewed in the direction of a designated primary flow streaming through the turbomachine, the vane disks have a front and a rear surface region. In a nominal and/or a maximum open position of the guide vanes, the front and/or the rear surface region of at least one of the vane disks has an offset from the inner ring surface that is radially disposed (relative to a central axis of the inner ring).

A method of making a master cure tool for applying a texture to an aerodynamic surface includes the steps of: providing a foil which is metallic and has a textured surface; applying the foil to a forming surface of a rigid forming tool which is compound curved, and plastically deforming the foil to conform to the forming surface, so as to define a foil layer; annealing the foil layer using heat or a combination of heat and pressure; and bonding the foil layer to a support body, thereby defining the master cure tool.

Gas turbine engine (GTE) compressor sections and compressor intake ducts are provided having Soft Foreign Object debris (SFOD) endwall treatments, which reduce peak damage to GTE components in the event of SFOD ingestion. In embodiments, the GTE compressor section includes a compressor rotor and a compressor intake duct. The compressor intake duct includes an intake flow passage, which extends through compressor intake duct to the compressor rotor. A first duct endwall extends around a centerline of the flow passage to bound a peripheral portion of the intake flow passage. An SFOD endwall treatment includes topological features formed in or otherwise provided on the first duct endwall. The topological features of the SFOD endwall treatment are configured such that SFOD impacting the topological features is directed in a radially inward direction toward the flow passage centerline prior discharge of the SFOD from the intake flow passage and into the compressor rotor.

The invention relates to a profiled structure, elongated in a direction in which the structure has a length (L1) exposed to an airflow (U), and transversely to which the structure has a leading edge (164) and/or a trailing edge (165), at least one of which is profiled and has, along said direction of elongation, geometric serration patterns (28) defined by a succession of peaks (30) and troughs (32).

Along the profiled leading edge and/or trailing edge, the serration patterns (28) have a geometric pattern that is repeated in the direction of elongation (L1), the shape of which is stretched and/or contracted: transversely to the direction of elongation, and/or in the direction of elongation.

This composite material structure is provided with: a first composite member arranged facing a heating element , the first composite member including PAN-based carbon fibers; a second composite member arranged between the heating element and the first composite member, the second composite member including pitch-based carbon fibers; and a cushioning element provided between the first composite member and the second composite member, the cushioning element being joined to each of the first composite member and the second composite member, and having lower rigidity than those of the first composite member and the second composite member. The first composite member is provided so as to be linked to an adjacent structure, while the second composite member and the cushioning element are provided so as to be separated from the structure.

A seal assembly includes a seal arc segment that defines first and second seal supports and radially inner and outer sides with the radially outer side including radially-extending sidewalls and a radially inner surface that joins the radially-extending sidewalls. The radially-extending sidewalls and the radially inner surface define a pocket. The seal assembly includes a carriage that defines first and second support members with the first support member supporting the seal arc segment in a first ramped interface and the second support member supporting the seal arc segment in a second ramped interface. The radially inner surface has a higher surface roughness than the radially extending sidewalls.

A bearing includes a bearing sleeve with a first portion and a second portion adjacent to the first portion. A bump foil extends along an inner face of the first portion of the bearing sleeve and a metal mesh extends along an inner face of the second portion of the bearing sleeve. A top foil extends along an inner face of the bump foil of the first portion and the metal mesh of the second portion.