A three-dimensional auxetic structure, comprising a plurality of adjoining hollow cells, each hollow cell having cell walls and a transversal cross section of the plurality hollow cells following a two-dimensional auxetic pattern, each cell wall comprising folding lines parallel to a plane containing the auxetic pattern such that peaks and valleys are defined in the cell walls and the cell walls being foldable along the folding lines.

The invention relates to an aircraft turbine engine module (10), comprising a degassing tube (14) and an ejection cone (12). The tube end the cone comprise centring means engaging together. The invention also relates to a locating and adjusting tool for assembling said module.

A polyhedral-sealed article is disclosed including an article having a surface and a polyhedral seal layer disposed on the surface. The polyhedral seal layer includes a polyhedral structure having a plurality of polyhedral units. The polyhedral seal layer further includes at least one of a composition including an HTW composition, a heterogeneous pattern of the polyhedral structure, an orientation of the polyhedral structure extending from the surface at non-orthogonal angle, and at least one polyhedral unit conformation other than a hexagonal prism. A method for forming the polyhedral-sealed article is disclosed including forming a polyhedral seal layer by binder jet additive manufacturing and disposing the polyhedral seal layer on a surface of an article.

A lock plate of a bladed rotor arrangement is hollow. The bladed rotor arrangement comprises is a bladed turbine rotor of a gas turbine engine. The hollow lock plate has reduced weight compared to a solid lock plate and reduces the centrifugal load on the rim of the rotor and reduces the stresses in the lock plate groove on the rotor blade and hence increases the working life of the rotor and the working life of the rotor blade respectively. The lock plate may have radially extending chambers and openings to provide a flow of coolant onto the rotor posts of the rotor.

In an embodiment, a blower for a heating, ventilation, and air conditioning system includes a blower wheel and a housing. The blower wheel includes backward-curved blades configured to rotate in a rotational plane. The housing forms an at least hexagonal cross-section around at least a portion of the rotational plane, where the blower wheel is positioned within the housing such that there exists a first distance and a second distance. The first distance is measured radially outward from a center of the blower wheel to a first side of the at least hexagonal cross-section. The second distance is measured radially outward from the center of the blower wheel to a second side of the at least hexagonal cross-section. The second distance forms a an acute angle with the first distance. The first distance and the second distance are unequal and less than a diameter of the blower wheel.

In an embodiment, a blower for a heating, ventilation, and air conditioning system includes a blower wheel and a housing. The blower wheel includes backward-curved blades configured to rotate in a rotational plane. The housing forms an at least hexagonal cross-section around at least a portion of the rotational plane, where the blower wheel is positioned within the housing such that there exists a first distance and a second distance. The first distance is measured radially outward from a center of the blower wheel to a first side of the at least hexagonal cross-section. The second distance is measured radially outward from the center of the blower wheel to a second side of the at least hexagonal cross-section. The second distance forms a an acute angle with the first distance. The first distance and the second distance are unequal and less than a diameter of the blower wheel.

A gas turbine engine component (10), having: a base layer (60) including an array (110) of pockets (52) separated by raised ribs (36), and a film cooling hole (70) through the base layer in each pocket; and a cover sheet (62) diffusion bonded to the raised ribs and including an impingement hole (72) for each pocket of the array of pockets. The raised ribs include a thickness (104) that is less than half of a smallest dimension (96) of the pocket. The component is configured to receive combustion gases from a combustor and accelerate and deliver the combustion gases onto a first row of turbine blades without a turning vane.

A gas turbine engine component includes a passage and a wall adjacent the passage. The wall includes a first side bordering the passage and a second side opposite the first side. The second side includes an array of cells. The wall also includes an array of channels. Each of the channels is located proximate a corresponding one of the cells. A coating is disposed over the cells. When the coating degrades the channels open to permit impingement air flow through the channel onto sidewalls of the cells.

A brush seal for a gas turbine, in particular an aircraft engine, is disclosed. The brush seal includes a support ring which has a support plate and a support structure, where the support structure is arranged downstream with respect to the support plate. The brush seal also includes bristles which are arranged upstream with respect to the support ring, where ends of the bristles protrude radially inward beyond the support plate. The support structure yields when a scraping force acting radially outward occurs on a first lateral surface of the support structure, where the first lateral surface is directed radially inward, and the support structure does not yield when an axial operating force occurs on a second lateral surface of the support structure.

Turbine engine (80) components, such as blades (92), vanes (104, 106), ring segment 110 abradable surfaces 120, or transitions (85), have vertically aligned engineered surface features (ESFs) (632, 634) and furcated engineered groove features (EGFs) (642, 652). A planform pattern of EGFs (642, 652) is cut into the outer surface of the component's thermal barrier coating (TBC). The EGF pattern includes a planform pattern of overlying vertices (644) respectively in vertical alignment with an underlying corresponding ESF (632, 634). At least three respective groove segments (642, 652, 642) within the EGF pattern (640) converge at each respective vertex (644) in a multifurcated pattern, so that crack-inducing stresses are attenuated in cascading fashion, as the stress (.sub.A) is furcated (.sub.B, .sub.C) at each successive vertex juncture.