A compressor rotor for a gas turbine engine has blades circumferentially distributed around and extending a span length from a central hub. The blades include alternating first and second blades having airfoils with corresponding geometric profiles. The airfoil of the first blade has a coating varying in thickness relative to the second blade to provide natural vibration frequencies different between the first and the second blades.

An airfoil is disclosed. The airfoil may comprise a leading edge, a body portion and a trailing edge formed from a high-modulus plating. The body portion of the airfoil may be formed from a material having a lower elastic modulus than the high-modulus plating. The high-modulus plating may improve the stiffness of the trailing edge, allowing for thinner trailing edges with improved fatigue life to be formed.

A method is provided, for manufacturing a component of a turbomachine, in particular a blade, in which initially a shell (6) including an interior cavity (7) corresponding to the outer contour of the component is manufactured from an intermetallic TiAl material, and subsequently a Ti alloy in powder form is filled into the cavity, and the cavity with the filled-in Ti alloy powder is tightly sealed, the tightly sealed shell (6) including the enclosed titanium alloy powder being subsequently processed into a component of the turbomachine using hot isostatic pressing. Alternatively, the invention relates to a method for generatively manufacturing a component including a shell made from a TiAl alloy and a core made from a Ti alloy. In addition, the invention relates to a correspondingly manufactured component.

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.

A method for repairing a fan casing in which the inner surface is damaged, includes attaching a reinforcement element to the fan casing, the reinforcement element being attached to the outer surface of the fan casing opposite the damage.

A composite component and a plated polymer component are disclosed. The composite component may comprise a body portion formed from an organic matrix composite, a first metal coating applied to a surface of the body portion, and an outer metal layer on the first metal coating that is erosion-resistant. The plated polymer component may comprise a polymer substrate, a metal plating layer applied to a surface of the polymer substrate, and at least one selectively thickened region in the metal plating layer. The at least one selectively thickened region may assist in protecting the plated polymer component against wear and/or erosion.

The present invention relates to cathodes electrodes compositions suitable to provide a pumping mechanism which exhibits an extremely high pumping speed and capacity of noble gas suitable to be used in several vacuum devices as for example sputter ion vacuum pumping systems comprising them as active element.

A vane stage includes an arcuate platform defining a axial centerline axis having a pair of flanges that extend radially inward from the platform. The flanges are axially spaced from one another and from respective forward and aft ends of the platform. The vane stage includes a vane extending radially outward from the platform and a seal carrier mounted to the flanges of the platform. A method for constructing a vane stage includes sliding a seal carrier between flanges of an arcuate platform. Each flange includes at least a pair of through holes and interfaces with a respective axial side of the seal carrier. The method includes drilling through holes in each axial side of the seal carrier by using the through holes of each flange as guides.

An airfoil including an airfoil body, a recessed portion of a first depth in a first side of the airfoil body, the recessed portion including a plurality of pockets of a second depth located within the recessed portion and ribs of the first depth located between the pockets, a cover configured to fit into the recessed portion such that an interior surface of the cover engages the ribs and an exterior surface of the cover is about flush with an exterior surface of the first side of the airfoil body, and a high energy beam weld configuration extending through the cover and into the ribs and positioned to attach the cover to the ribs.

A weld clad layer having a substantially equiaxed grain microstructure may be formed by forming a repair area in a substrate, depositing a first layer of laser deposition spots in the repair area, and depositing a second layer of laser deposition spots over the first layer of laser deposition spots. The first layer of laser deposition spots may comprise a first laser deposition spot and a second laser deposition spot adjacent to the first laser deposition spot. The first laser deposition spot may solidify prior to deposition of the second laser deposition spot. The first layer of laser deposition spots may comprise titanium or titanium alloy.