A disclosed fan system includes a housing having side walls, an inflow side, and an outflow side; a fan secured in the housing by a mounting; and a backflow blocker mounted to the side walls within the housing on the outflow side of the housing partially blocking a cross-sectional area of the outflow side. The backflow blocker is positioned approximately centrally in a flow path of the housing and is configured to block part of an airflow cross section such that, between side walls of the housing and side walls of the backflow blocker, an annular duct is formed as an air passage. Further, the backflow blocker has a thickness that is greater than 5% of a width of the housing, and is less than 20% of an axial design height of the fan system.

In a manufacturing method of a turbine housing having an exhaust gas flow path, the exhaust gas flow path in the turbine housing is formed of a sheet-metal-made divided body and a cast-metal-made divided body, the sheet-metal-made divided body is formed by press molding a sheet metal material, and the cast-metal-made divided body is molded by casting, when the cast-metal-made divided body is cast, one end of the sheet-metal-made divided body is cast into the cast-metal-made divided body by melting the one end of the sheet-metal-made divided body such that the original shape thereof is disappeared.

A vibrational dampening element is attached to a component and configured to adjust the amplitude of oscillations of the component. The vibrational dampening element includes a mass. The mass includes a main body and a member extending from the main body. A casing that encapsulates the mass. A fluidic chamber defined between the mass and the casing. A first fluidic portion is disposed between a first side of the mass and the casing. The first fluidic portion includes a first accumulator portion directly neighboring the member. A second fluidic portion is disposed between a second side of the mass and the casing. The second fluidic portion includes a second accumulator portion directly neighboring the member. The first accumulator portion is in fluid communication with the second accumulator portion. The vibrational dampening element further includes a primary passage that extends between the first fluidic portion and the second fluidic portion.

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.

Turbine housing assemblies and related fabrication methods are provided. A turbine housing assembly includes a bearing flange, a tongue member, a first sheet metal structure providing an inner contour of an inlet passage and joined to the tongue member, and a second sheet metal structure including an inlet portion providing an outer contour of the inlet and a volute portion providing an outer contour of a volute in fluid communication with the inlet. The volute portion is joined to the tongue member to define the volute, and the inlet portion of the second sheet metal structure is joined to the first sheet metal structure to define the inlet passage.

A structure for assembling turbine blade seals, which includes a turbine blade including an airfoil, a platform, and a root, a turbine rotor disk to which the root of the turbine blade is mounted, a seal plate mounted between the platform and one side of the turbine rotor disk to seal a cooling channel defined within the root and the platform, and an insertion pin inserted through the turbine rotor disk to fix the seal plate to the turbine rotor disk by supporting the seal plate, wherein the turbine rotor disk has a mounting groove into which a radially inner end of the seal plate is inserted, and the seal plate has a jaw portion radially supported by a stepped portion of the mounting groove.

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.

In an aspect there is disclosed, a fan arrangement for a duct, the fan arrangement including a housing having an inlet and an outlet adapted to communicate air with the duct and an axially rotatably driven impeller supported within the housing between the inlet and the outlet. The impeller includes a hub carrying a plurality of blades that span in a radial direction outwardly of the hub, the plurality of blades being shaped to urge air between the inlet and the outlet. The plurality of blades may have a tip solidity ratio in the range of about 0.8 to 1.2, and each of the plurality of blades may have a twist angle between a root and a tip thereof in the range of about 15 to 30 degrees and a substantially constant thickness. An impellor, a blade, ventilation system and related methods are also disclosed.

A blade containment assembly for a gas turbine engine comprises a casing having a first casing member surrounding a set of rotor blades and a second casing member extending axially from the first casing member. The first casing member has an outer annular wall welded to the second casing member at a weld joint disposed in a blade containment zone of the casing and an inner containment ring spaced radially inwardly from the outer annular wall and extending axially from a first location forward of the weld joint to a second location aft of the weld joint.

Various embodiments of an airfoil and machines with airfoils are disclosed. The airfoils include a thicker leading airfoil portion and a thinner trailing airfoil portion. In one embodiment, the leading airfoil portion is formed by bending a body of the airfoil back toward itself. In another embodiment, the leading airfoil portion has a solid geometry and includes two elliptic surfaces. To prevent detachment of airflow, the leading airfoil portion includes at least two arc portions or surfaces that act to direct the airflow down to the trailing airfoil portion in a manner that stabilizes vortexes that may form in the region of changing thickness.