A vacuum device comprising at least one component having a portion which, during operation of the vacuum device, is in contact with a vacuum and which is coated at least in part by a layer which absorbs gas particles, in particular with a layer of a no-evaporable getter (NEG) material.

A method of immobilizing a contaminant within a component includes identifying the contaminant. The component is thermally processed via a specific thermal cycle related to the contaminant. The specific thermal cycle is performed within an inert environment relative to a substrate. The specific thermal cycle is configured to effect a controlled evaporation of volatiles of the contaminant and a controlled coking of remaining contaminant.

A gas turbine engine has a fan tip air angle and/or a fan blade tip air angle in a defined range to achieve improved over all performance, taking into account fan operability and/or bird strike requirements as well as engine efficiency. The defined ranges of fan tip air angle and/or a fan blade tip air angle may be particularly beneficial for gas turbine engines in which the fan is driven by a turbine through a gearbox.

An electric conduction structure for conducting and diverting electric current from a vane main body of an cutlet guide vane into en exterior support structure is comprised of: a sheath of a metal covering a leading edge of the vane main body; and an electrically conductive pad of the metal comprising a contact portion so dimensioned as to have an overlap with an end of the sheath, and a washer portion into which a bolt for being tightened into the support structure is insertable, wherein any joints of a weld, a spot-weld, a solder, a bond by an electrically conductive paste and a crimp establish connection between the end of the sheath and the contact portion.

A method of producing a gas turbine engine fan blade having a geometric configuration is provided. The method includes: plastically deforming an initial substrate comprised of a first metallic material into a formed substrate; depositing a second metallic material onto the formed substrate using an additive manufacturing process to produce a blade blank, which depositing includes: additively depositing second metallic material to at least one of the first face surface or the second face surface of the formed substrate adjacent the first end surface, to form a root portion; additively depositing second metallic material to at least one of the first face surface or the second face surface of the formed substrate between the root portion and the second end surface to form an airfoil portion; and shaping the blade blank into the geometric configuration.

A device for fastening a downstream end of an air inlet on a fan casing of an aircraft turbojet engine nacelle is provided. The device includes an acoustic shroud, a first flange coupled to the fan casing, a second L-shaped flange having a base coupled to the acoustic shroud, and a collar linked to the first flange. The acoustic shroud extends from an upstream segment to a downstream segment which defines an inner skin and an outer skin that encloses an acoustic panel. The collar further includes a protrusion that extends from the outer skin to the downstream segment.

A multi-piece fan spacer for a gas turbine engine includes at least one lug comprising a platform portion, a connection portion radially inward of the platform portion, and a support connecting the platform portion to the connection portion. The multi-piece fan spacer includes a plurality of platforms. Each of the platforms is connected to at least one axially adjacent platform portion.

A turbomachine rotor blade, which includes a body radially extending and an insert covering the body tip, the insert being made of a first portion radially covering the blade tip and of a second portion partly covering the intrados face of the blade. The cross-section of the insert along a radial plane with respect to an axis of a rotor is corner-shaped and the first portion of the insert extends tangentially with respect to the main axis of the rotor and the second portion extends globally radially with respect to the main axis of the rotor.

Aspects of the disclosure are directed to a first chip ring that includes a first through slot, a second chip ring that includes a second through slot, and a component disposed between the first chip ring and the second chip ring that includes a component through slot, where the first, second and component through slots are coaxial along a slot axis this is oriented at a non-zero valued angle relative to a planar surface of the component facing at least one of the first and second chip rings.

Light weight fan blades for turbofan jet engines are disclosed. The fan blades may be fabricated from an aluminum alloy. To enhance the hardness of the leading edge of the fan blade, a titanium sheath may be attached to the leading edges of the fan blades. To prevent galvanic coupling between the titanium and the aluminum, a polymeric liner may be disposed between the protective titanium sheath and the aluminum fan blade. The liner may be fabricated from a polymer material, such as a polyimide or another high performance polymer.