Abstract: A sealing process includes impregnating an oxide layer of an anodized metal with a corrosion inhibitor by contacting the oxide layer with a first corrosion inhibitor solution at a first temperature and sealing the impregnated oxide layer of an anodized metal by contacting the impregnated oxide layer with a second corrosion inhibitor solution at a second temperature, wherein the first corrosion inhibitor solution has a corrosion inhibitor concentration greater than the second corrosion inhibitor solution and the first temperature is less than the second temperature.

Abstract: Disclosed herein is a blade for a turbine comprising a blade cover; a blade body; and a layer of adhesive disposed between the blade cover and the blade body; where the layer of adhesive comprises a first adhesive region and a second adhesive region; where the first adhesive region comprises an adhesive that is chemically different from an adhesive used in the second adhesive region.

Abstract: An airfoil element including an airfoil having a pressure side and a suction side, an aluminum alloy substrate and a coating system atop the substrate, said coating comprising in at least one location an anodize layer (24) having a thickness (TA) of 1.0 to 5.0 micrometer, a sealant (36) filling at least 5.0% of porosity in the anodize layer or at least 0.7% of an apparent volume within a height of the anodize layer, a sealant primer (40) filling 50.0% of porosity in the anodize layer or at least 6.5% of an apparent volume within a height of the anodize layer and extending at least flush to the anodize layer, a second primer (44) over the sealant primer having a thickness (TS) of 5.0 to 50 micrometer and a polymeric coating (48) having a thickness (TT) of 10.0 micrometer to 1.0 millimeter.

Abstract: A sealing process includes impregnating an oxide layer of an anodized metal with a corrosion inhibitor by contacting the oxide layer with a first corrosion inhibitor solution at a first temperature and sealing the impregnated oxide layer of an anodized metal by contacting the impregnated oxide layer with a second corrosion inhibitor solution at a second temperature, wherein the first corrosion inhibitor solution has a corrosion inhibitor concentration greater than the second corrosion inhibitor solution and the first temperature is less than the second temperature.

Abstract: Disclosed herein is a blade for a turbine comprising a blade cover; a blade body; and a layer of adhesive disposed between the blade cover and the blade body; where the layer of adhesive comprises a first adhesive region and a second adhesive region; where the first adhesive region comprises an adhesive that is chemically different from an adhesive used in the second adhesive region.

Abstract: Disclosed herein is a blade for a turbine comprising a blade cover; a blade body; and a layer of adhesive disposed between the blade cover and the blade body; where the layer of adhesive comprises a first adhesive region and a second adhesive region; where the first adhesive region comprises an adhesive that is chemically different from an adhesive used in the second adhesive region.

Abstract: A sealing process includes impregnating an oxide layer of an anodized metal with a corrosion inhibitor by contacting the oxide layer with a first corrosion inhibitor solution at a first temperature and sealing the impregnated oxide layer of an anodized metal by contacting the impregnated oxide layer with a second corrosion inhibitor solution at a second temperature, wherein the first corrosion inhibitor solution has a corrosion inhibitor concentration greater than the second corrosion inhibitor solution and the first temperature is less than the second temperature.

Abstract: The present disclosure provides methods and systems for the bonding of dissimilar substrates. For example, a first substrate may be coupled to a second substrate by a composite joint between the first substrate and the second substrate. The composite joint may be comprised of a first adhesive material and a second adhesive material. The first adhesive material may be disposed on the first substrate, and the second adhesive material may be disposed to the first adhesive material. The composite joint between the first substrate and the second substrate may provide an isolation layer therebetween, preventing galvanic corrosion.

Abstract: A blade comprises an airfoil extending from a trailing edge to a leading edge. The airfoil includes a body formed of an aluminum containing material. A sheath is at the leading edge and is formed of a titanium containing material. A sandwich is positioned intermediate the sheath and the airfoil body, the sandwich including an outer adhesive layer adjacent the sheath, an intermediate fabric layer and an inner adhesive layer adjacent the body. A gas turbine engine is also disclosed.

Abstract: An airfoil for a gas turbine engine is disclosed. The airfoil may include a first side, and a second side opposite the first side. The first side and the second side may extend axially from a leading edge to a trailing edge and radially from a base to a tip. The tip may include an oblique surface between the first side and the second side.

Abstract: A rotating component includes an airfoil section with a free end, the airfoil section being formed of a composite core with a metallic skin and an abrasive coating applied to the free end.

Abstract: A method of forming an airfoil includes placing a material onto a die that is heated to a predetermined temperature to pre-heat the material to a first temperature, while the die is in an open position. The method further includes closing the die at a predetermined rate and holding the die in a closed position for a predetermined period of time at a first force. The method still further includes removing the part from the die, cooling the die, placing the part onto the die, and closing the die at a second force.

Abstract: A fan of a gas turbine engine includes a plurality of fan blades secured to a rotor, each of the plurality of fan blades having an airfoil secured to the rotor at one end, wherein the airfoil comprises pockets filled with an elastomeric composite.

Abstract: An abrasive tip comprises an additive layer having an additive; the additive is configured to prevent adhesion of an organic component from an abradable seal onto an abrasive blade tip.

Abstract: An abrasive tip comprises an additive, the additive is configured to prevent adhesion of an organic component from an abradable seal onto an abrasive blade tip.

Abstract: An airfoil member (100) comprising has a substrate (120) along at least a portion of an airfoil (102) of the airfoil member. A sheath (122) has a channel (144) receiving a portion (160) of the substrate. A scrim (200) is between the substrate and the sheath. A spacer (220) is between the sheath and the substrate and has a plurality of spaced-apart portions (232, 234) with gaps between the spaced-apart portions.

Abstract: A method is provided for manufacturing a blade. The blade comprises an airfoil (100) having: a root end and a tip (106); a metallic substrate (102) along at least a portion of the airfoil; and an anodized layer (154). The method comprises roughening the tip to form protrusions (158?; 402?) and anodizing to form the anodized layer so that the protrusions form an abrasive (156; 400).

Abstract: An airfoil member (100) comprising has a substrate (120) along at least a portion of an airfoil (102) of the airfoil member. A sheath (122) has a channel (144) receiving a portion (160) of the substrate. A plurality of separate spacers (320; 380; 400) are between the sheath and the substrate and have a plurality of gaps between the spacers.

Abstract: An airfoil includes an airfoil body that extends at least between leading and trailing edges, first and second sides, and radially inner and outer ends. The airfoil body includes an aluminum alloy that has a controlled crystallographic texture with respect to a predefined three-dimensional coordinate system. The airfoil can be used in the fan of a gas turbine engine.

Abstract: A turbine engine rotor component has a Ti-based first member (66) circumscribing an axis (500) and has either a circumferential array of integrally formed airfoils (62) or a circumferential array of blade retention features. A TiB particulate reinforced second member (90) also circumscribes the axis.