Abstract: A method of coating a component including aluminizing an array of internal passageways within the component; and chromizing a portion of the array of internal passageways within the component. A component, including an airfoil having an array of aluminized internal passageways, the array of aluminized internal passageways chromized up to a demarcation.

Abstract: A method for depositing a coating of a source material onto a panel is disclosed. The method includes providing a cathodic arc, the cathodic arc including a target surface, the target surface disposed along a target deposition axis and able to emit the source material as a generally cloud of source material vapor and a generally conical stream of liquid particles of the source material. The method further includes positioning the panel relative to the target surface based on a deposition angle, the deposition angle being between the target surface and an outer limit of the generally conical stream of liquid particles o the source material. The method may further include emitting the source material from the target surface as the generally conical cloud of source material vapor and coating the edge with the cloud of source material vapor to provide an edge coating.

Abstract: A method includes casting a metallic material (56) in a mold (20) containing a core, the core having a substrate (40, 44) coated with a coating (42). A removing of the metallic material from the mold and decoring leaves a casting having a layer formed by the coating. The coating has a ceramic having a porosity in a zone (50) near the substrate less than a porosity in a zone (52) away from the substrate.

Abstract: A method includes casting a metallic material (56) in a mold (20) containing a core, the core having a substrate (40, 44) coated with a coating (42). A removing of the metallic material from the mold and decoring leaves a casting having a layer formed by the coating. The coating has a ceramic having a porosity in a zone (50) near the substrate less than a porosity in a zone (52) away from the substrate.

Abstract: A method of forming a component by investment casting includes disposing at least a portion of an investment casting pin within a core. The investment casting pin includes a ceramic base pin having a perimeter and a length extending perpendicular to the perimeter and a sacrificial coating disposed about the perimeter of the ceramic base pin along at least a portion of the length of the ceramic base pin. A metal casting is formed around the core. The core and the sacrificial coating are leached with a leaching solution and the investment casting pin is removed from the metal casting.

Abstract: A method of coating a component including aluminizing an array of internal passageways within the component; and chromizing a portion of the array of internal passageways within the component. A component, including an airfoil having an array of aluminized internal passageways, the array of aluminized internal passageways chromized up to a demarcation.

Abstract: An embodiment of an apparatus includes means for peripherally welding a cavity-back blade and a cover of the cavity-back blade to form a 3-dimensional hollow blade assembly, and a plurality of bellows contained in one or both of a first die half and a second die half receiving the 3-dimensional hollow blade assembly. The plurality of bellows are disposed within the region defined around or inward of the peripherally welded interface of the cover and the blade. At least a portion of the plurality of bellows are arranged in a manner to provide pressure to the cover at approximately a 90 degree angle to each of a plurality of nodes, each node defined by an intersection of two or more ribs in the cavity-back blade.

Abstract: A method of forming a component by investment casting includes disposing at least a portion of an investment casting pin within a core. The investment casting pin includes a ceramic base pin having a perimeter and a length extending perpendicular to the perimeter and a sacrificial coating disposed about the perimeter of the ceramic base pin along at least a portion of the length of the ceramic base pin. A metal casting is formed around the core. The core and the sacrificial coating are leached with a leaching solution and the investment casting pin is removed from the metal casting.

Abstract: A method for depositing a coating of a source material onto a panel is disclosed. The method includes providing a cathodic arc, the cathodic arc including a target surface, the target surface disposed along a target deposition axis and able to emit the source material as a generally cloud of source material vapor and a generally conical stream of liquid particles of the source material. The method further includes positioning the panel relative to the target surface based on a deposition angle, the deposition angle being between the target surface and an outer limit of the generally conical stream of liquid particles o the source material. The method may further include emitting the source material from the target surface as the generally conical cloud of source material vapor and coating the edge with the cloud of source material vapor to provide an edge coating.

Abstract: A method for depositing a coating of a source material onto a panel is disclosed. The method includes providing a cathodic arc, the cathodic arc including a target surface, the target surface disposed along a target deposition axis and able to emit the source material as a generally cloud of source material vapor and a generally conical stream of liquid particles of the source material. The method further includes positioning the panel relative to the target surface based on a deposition angle, the deposition angle being between the target surface and an outer limit of the generally conical stream of liquid particles o the source material. The method may further include emitting the source material from the target surface as the generally conical cloud of source material vapor and coating the edge with the cloud of source material vapor to provide an edge coating.

Abstract: A coating method includes vaporizing a portion of a cathode to form a metallic plasma, and directing the metallic plasma toward the workpiece. A first magnetic field generator, disposed in a first electrically conductive portion of a first stinger cup, is operated to steer the electrical arc about at least one evaporative surface of the cathode. a second portion of the electrically conductive stinger cup is selectively contacted with the cathode, and the first portion of the first stinger cup is spaced from the second portion from by a thermally insulating layer therebetween. The thermally insulating layer is disposed directly between the first magnetic field generator and the cathode when the first stinger cup is in contact with the cathode.

Abstract: 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.

Abstract: A coating system for coating a part (10), such as a turbine blade or vane, has a mask (14) positioned adjacent to a first portion (16) of the part (10) to be coated and a mechanism (30) for moving the mask (14) relative to the part (10). The mechanism (30) may be a gear mechanism or a magnetic mechanism.

Abstract: A method of coating a component including aluminizing an array of internal passageways within the component; and chromizing a portion of the array of internal passageways within the component. A component, including an airfoil having an array of aluminized internal passageways, the array of aluminized internal passageways chromized up to a demarcation.

Abstract: An embodiment of an apparatus includes means for peripherally welding a cavity-back blade and a cover of the cavity-back blade to form a 3-dimensional hollow blade assembly, and a plurality of bellows contained in one or both of a first die half and a second die half receiving the 3-dimensional hollow blade assembly. The plurality of bellows are disposed within the region defined around or inward of the peripherally welded interface of the cover and the blade. At least a portion of the plurality of bellows are arranged in a manner to provide pressure to the cover at approximately a 90 degree angle to each of a plurality of nodes, each node defined by an intersection of two or more ribs in the cavity-back blade.

Abstract: A friction interface in a gas turbine engine includes an abradable component, such as a seal, and an abrasive component, such as a blade tip, in rubbing contact with each other. The abradable component is composed of a polymer matrix composite and the abrasive component is composed of a metal matrix with hard particles dispersed through the metal matrix. The metal matrix is an aluminum alloy and the hard particles are selected from oxides, nitrides, carbides, oxycarbides, oxynitrides, diamond and combinations thereof.

Abstract: A blade outer airseal has a body comprising: an inner diameter (ID) surface; an outer diameter (OD) surface; a leading end; and a trailing end. The airseal body has a metallic substrate and a coating system atop the substrate along at least a portion of the inner diameter surface. At least over a first area of the inner diameter surface, the coating system comprises an abradable layer comprising a metallic matrix and a solid lubricant; and the metallic matrix comprises, by weight, ?35% nickel, 12.0-20.0% cobalt, 5.0-15.0% aluminum, and 5.0-15.0% chromium.

Abstract: A blade includes an airfoil section extending between leading and trailing edges, first and second opposed sides each joining the leading and trailing edges, and an inner end and a free tip end. The airfoil section is formed of a metal-based material with a polymeric overcoat on at least one of the leading edge, trailing edge, first side and second side. The airfoil section includes an abrasive tip at the free tip end. The abrasive tip has a composition selected with respect to heat-induced delamination of the polymeric overcoat from frictional heat generated during rubbing of the abrasive tip.

Abstract: 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.

Abstract: An apparatus for use in a physical vapor deposition coating process includes a chamber, a crucible configured to hold a ceramic coating material in the chamber, an energy source operable to heat the interior of the chamber, a fixture for holding at least one substrate in the chamber, an actuator operable to rotate the fixture, and a controller configured to establish a plume of the ceramic coating material in the chamber to deposit the ceramic coating material from the plume onto the at least one substrate and form a ceramic coating thereon, and during the deposition, rotate the at least one substrate at a rotational speed selected with respect to deposition rate of the ceramic coating material onto the at least one substrate.