A method includes mounting a hollow cylinder on a turntable, positioning an additive-manufacturing deposition tool at a surface of the hollow cylinder, and rotating the hollow cylinder on the turntable while depositing material on the hollow cylinder with the deposition tool. Further, a method includes making an opening in a wall of the hollow cylinder, forming a part to fit in the opening, and welding the part to the hollow cylinder such that the part fills the opening. The hollow cylinder has an inner radius and an outer radius, and the part is formed with an inner radius of curvature and an outer radius of curvature substantially similar to the inner radius and outer radius, respectively, of the hollow cylinder when the part is positioned in the opening.

The proposed solution relates, in particular, to an engine component having at least one first loading zone, which is designed for dynamic loads arising at the engine component when the engine component is correctly built into an engine and when the engine is operating, and a second loading zone, which is provided spaced at a distance from the first loading zone on the engine component and likewise is designed for dynamic loads arising at the engine component when the engine component is correctly built into an engine and when the engine is operating. The proposal is, in particular, that at least one spatially delimited modification zone with introduced internal tensile stress is formed on the engine component, via which zone a crack propagating in the engine component is guided to the and/or within the second loading zone.

A system for deep rolling a fan blade including a shaft assembly disposed along a first axis; a hub connected to a distal end of the shaft assembly, the hub having an upper hub portion and a lower hub portion extending along a second axis, the second axis forming an angle relative to a first axis; a roller disk joined to the lower portion of the hub, the roller disk configured to contact a fan blade; a fixture supporting the fan blade; the fixture comprising a body supporting a pivot clamp attached to the body with a pivot; a support attached to the body, the support is configured to engage an airfoil portion of the fan blade; a receiver formed in the body for supporting a root of the fan blade; and a shoulder attached to the body configured to support a platform portion of the fan blade.

Provided is a bilateral ultrasonic rolling processing track coordination method for a blade surface, the method comprising: step S1, performing layering processing on a blade to acquire a contour curve of A-shaped and n-shaped blade edges of a blade model at different heights; step S2: determining the endpoints of a blade processing track; and step S3: planning the thickness and the rotation angle of the blade, comprising: step S31, solving a main direction angle .sub.main of the contour curve; step S32, solving the thickness d of the blade; step S33, solving a rotation angle required by blade processing when the blade edge is A-shaped; and step S34, solving the rotation angle required by blade processing when the blade edge is n-shaped. According to the method, blade deformation generated by an ultrasonic rolling force is reduced, the processing efficiency is improved, and the blade processing precision is also improved.

A method for producing a contoured ring rolling product for a rotating application from a ring blank, with a ring rolling machine controlled in a process-monitored manner. At least one process window, extending over the rolling time, is defined in relation to preselected process parameters for the specific product on the basis of calibrating specimens brought into their final form by the ring rolling machine. The process window(s) monitored during the process is/are determined by the process parameters of calibrating specimens which produced rolled products meeting the requirements demanded of the ring rolling product. The preselected process parameters comprise at least two of ring growing rate, axial rolling force, radial rolling force, rolling time, and ring blank temperature. Ring blanks are subsequently rolled in a contoured manner with parameters of the rolled blanks being recorded with reference to the preselected process parameters and evaluated to ascertain whether they lie within the predefined process window(s), thereby determining whether they are accepted for further machining and/or processing.

Aspects of the disclosure are directed to a seal configured to interface with at least a first component and a second component of a gas turbine engine. A method for forming the seal includes obtaining an ingot of a fine grained, or a coarse grained, or a columnar grained or a single crystal material from a precipitation hardened nickel base superalloy containing at least 40% by volume of the precipitate of the form Ni3(Al, X), where X is a metallic or refractory element, and processing the ingot to generate a sheet of the material, where the sheet has a thickness within a range of 0.010 inches and 0.050 inches inclusive.

A hollow turbine airfoil or a hollow turbine casting including a cooling passage partition. The cooling passage partition is formed from a single crystal grain structure nickel based super alloy, a cobalt based super alloy, a nickel-aluminum based alloy, or a coated refractory metal.

A method of manufacturing a component from a nickel-based superalloy comprises the steps of: providing a vacuum induction casting furnace; positioning a component mould onto a chill plate within the furnace; casting a component blank; peening the surface of the component blank; applying a surface modification technique to the surface of the component blank; solution heat treating the component blank at or above the -solvus temperature for the superalloy; and precipitation heat treating the component blank.

Method of manufacturing of components used in the field of aviation aircraft and, specifically, an aircraft engine nacelle lipskin. Instead of spinning flat plates, this method uses spinning a cylinder, thus eliminating waste material. It also eliminates the need for rivet lines which results in better laminar flow. Further, there is a reduction of other costs in addition to reducing drag.

Aspects are directed to removing a portion of a component that includes wear to generate a void in the component, where a material of the component has a first microstructure, depositing a filler material in the void, subjecting the filler material to a cold working technique to compress the filler material, and applying a heat treatment to cause the filler material to have a second microstructure that is matched to the first microstructure. Aspects are directed to a case of an engine, including: a first portion with a first material that has a first microstructure, and a second portion with a second material that has a second microstructure, where the second microstructure is matched to the first microstructure, where the second material includes a plurality of layers, and where at least one layer of the plurality of layers includes a compressive residual stress.