Abstract: A method for peening a component of a gas turbine engine, or a module of a gas turbine engine, without removing the component from the assembled gas turbine engine or module includes blending the damaged area of the component, determining parameters for peening the damaged component, and peening the damaged component without removing it from the engine.

Abstract: A multi-level marketing system includes a holding company and a multi-level marketing company operated by the holding company, wherein the multi-level marketing company provides a product and/or service. A distributor buys the product and/or service from the multi-level marketing company, and one or more individuals purchase the product and/or service from one of the distributors.

Abstract: Novel materials and methods for repairing/reclassifying superalloy components are described herein. These materials are non-traditional blends of materials having a much higher base material content than traditional repair/reclassification materials. In embodiments used to repair/reclassify nickel-based components, these materials may comprise about 5-18.9 weight percent of a low melting point alloy and about 81.1-95 weight percent of a base material. In embodiments used to repair/reclassify cobalt-based components, these materials may comprise about 15-30 weight percent of a low melting point alloy and about 70-85 weight percent of a base material. These materials can be used to repair surface defects and/or build up worn or eroded areas of a component to meet precise dimensional and metallurgical requirements. These materials create robust repaired components having a dense, isothermally solidified structure having minimal borides and a high re-melt temperature.

Abstract: A method for depositing a first material on a substrate includes providing the substrate in a deposition chamber. A molten body is formed between the substrate and a source of the first material by melting one or more second materials. A flow of the first material is passed through the molten body and from the molten body to the substrate as a vapor flow. An essentially non-expending portion of the molten body comprises an alloy having a melting temperature below a melting temperature of the first material.

Abstract: A first component is bulk brazed to a second component. The bulk braze joint is inspected. Responsive to the inspection locating a defect site, the joint is laser brazed at the defect site.

Abstract: A Ti-based coating may have embedded defects. The defects may impart one or more structural weakness to the coating and coated part. The coating is subjected to a burnishing process to impart a residual compressive stress to mitigate one or more of these structural weaknesses.

Abstract: Novel materials and methods for repairing/reclassifying superalloy components are described herein. These materials are non-traditional blends of materials having a much higher base material content than traditional repair/reclassification materials. In embodiments used to repair/reclassify nickel-based components, these materials may comprise about 5-18.9 weight percent of a low melting point alloy and about 81.1-95 weight percent of a base material. In embodiments used to repair/reclassify cobalt-based components, these materials may comprise about 15-30 weight percent of a low melting point alloy and about 70-85 weight percent of a base material. These materials can be used to repair surface defects and/or build up worn or eroded areas of a component to meet precise dimensional and metallurgical requirements. These materials create robust repaired components having a dense, isothermally solidified structure having minimal borides and a high re-melt temperature.

Abstract: A method for repairing components comprises the steps of providing a component having a defect to be repaired and depositing an aluminum containing repair material over an affected area on a surface of the component so that the repair material plastically deforms and bonds to the affected area upon impact with the affected area and thereby covers the affected area.

Abstract: A method for depositing a first material on a substrate includes providing the substrate in a deposition chamber. A molten body is formed between the substrate and a source of the first material by melting one or more second materials. A flow of the first material is passed through the molten body and from the molten body to the substrate as a vapor flow. An essentially non-expending portion of the molten body comprises an alloy having a melting temperature below a melting temperature of the first material.

Abstract: A method for restoring blade dovetails to their original shape comprising the steps of removing damaged material from a blade dovetail at a damage site, physically depositing a metal at the damage site in an amount sufficient to replace the removed damaged material, and machining the blade dovetail to the original shape.

Abstract: The present invention relates to a self cleaning braze paste which is used in the repair of gas turbine engines. The braze paste comprises lithium fluoride in an amount sufficient to act as a flux which allows the braze material to flow into a crack or void in a part to be repaired up to an amount where there is no residual lithium or fluoride in the crack or void, preferably up to about 20% by volume, a gel binder in an amount up to about 15% by volume, and the balance comprising at least one of a nickel braze alloy and a cobalt braze alloy. In a preferred embodiment, the lithium fluoride is present in an amount from about 10% to about 15% by volume. The braze material of the present invention may be applied in a paste form or, alternatively, in a paint or tape form. A method for cleaning and repairing a braze joint is also disclosed.

Abstract: An abrasive, wear resistant layer is applied to the tip surface of a superalloy gas turbine blade by high temperature sintering operation which produces a high strength bond between the layer and the blade, minimizes gamma prime phase growth, and prevents recrystallization in the blade. Important features of the invention include removing plastic strain damage from the tip surface prior to the sintering operation, using induction heating techniques to sinter a layer of metal powder particles and ceramic particulates to the blade tip surface, and shielding the airfoil and root portion of the blade from the radiant heating source during the sintering operation while at the same time, conductively removing heat from the blade.

Abstract: A gas turbine engine blade has an abrasive material tip with a fused superalloy matrix and evenly distributed ceramic particulate. The matrix will have a desirable metallurgical structure characterized by fine dendrites and remanants of the original powder metal structure from which it was made. Due to the fusion of the tip, the peripheral edge will tend to be curved. To lessen the effect of thermal strains on such an abrasive tip, a sheath of a superalloy, such as a portion of the turbine blade substrate, extends along the side of the abrasive. The sheath may be present only in the thicker leading edge part of the blade airfoil.

Abstract: An abrasive material comprised of a metal matrix and evenly distributed ceramic particulates, is made by mixing powder metal with the ceramic powder and heating to a temperature sufficient to melt most, but not all of the powder. In this way the ceramic does not float to the top of the material, yet a dense material is obtained. A nickel superalloy matrix will have at least some remnants of the original powder metal structure, typically some equiaxed grains, along with a fine dendritic structure, thereby imparting desirable high temperature strength when the abrasive material is applied to the tips of blades of gas turbine engines. Preferred matrices have a relatively wide liquidus-solidus temperature range, contain a melting point depressant, and a reactive metal to promote adhesion to the ceramic.

Abstract: Fabrication techniques for making nickel boron stranded wire braze preforms are described. The techniques involve the provision of the wire material in a stranded form having a large surface to volume ratio. This general form consists of a plurality of fine wires, having the desired cross-sectional area, which may be twisted or braided to produce the preform.

Abstract: Fiber-reinforced titanium alloy composite materials and their manufacture are disclosed. Beta-titaium alloy foils are alternated with arrays or silicon carbide coated boron fibers and consolidated at a pressure of at least 22 ksi within the temperature range of 1250.degree.-1275.degree. F.