A base plate is a portion of a housing of a disk drive apparatus, including a base body defined by a metal die cast member, and an electrodeposition coating film covering at least a portion of a surface of the base body. The base body includes a bottom plate rectangular as viewed from an axial direction, and a pivot post. The bottom plate extends perpendicular to a rotation axis of a disk and a swing axis of a head. The rotation axis extends vertically. The swing axis is disposed in a different position from the rotation axis and extends vertically. The head reads or writes information from or to the disk. The pivot post protrudes upward from an upper surface of the bottom plate along the swing axis, and a portion of the die cast member is segregated.

A system for removing a heat check feature on an aluminum casting formed by a high pressure die casting process is provided. The system includes a laser source, a robotic arm, and a heat check sensor. The heat check sensor develops a surface profile of at least part of the casting and transmits heat check feature information to the laser source to project the beam of laser light thereon. The projection of the beam of laser light can be varied in time and power, which can depend on surface profile information obtained from the sensor. Once at least a portion of the heat check feature is removed, the casting is placed against another part such that the joint interface is primarily the portion where the heat checking has been removed. Self-piercing rivets are then driven into the casting and the part to permanently join them together.

The invention discloses an apparatus for repairing wheel tread with material increase, which comprises a slide rail, a rack, a case, a supporting device, a drive device, a wheel heating device, an ingot blank heating device and an agitation and output device; the rack is fixedly arranged above the slide rail, an upper end of the case is fixedly connected to an upper portion of the rack, the supporting device and drive device are both slidably connected to the slide rail, an output end of the drive device is fixedly connected to the wheels which are positioned below a semicircular notch and are located eccentrically relative to the semicircular notch. The wheel heating device is fixedly arranged below the case, the ingot blank heating device and the agitation and output device are both fixedly arranged in the case, the ingot blank heating device is communicated with the agitation.

The method of locating hole features so that old components can be replaced with new components and still match fit with the airframe includes the steps of adhering a bushing assembly into a fixture plate, rigidly attaching the fixture plate with the bushing assembly to the old component, heating the liquid metal above the liquid metal melting temperature such that the cylindrical drill bushing can move within the assembly, inserting an alignment pin within the cylindrical drill bushing such that the alignment pin is also inserted into an existing hole in the old component and the airframe, allowing the liquid metal to re-solidify; removing the alignment pin from the old component, replacing the old component with the new component, and using the re-solidified assembly as a drill guide for replacing holes in the new component.

The method of locating hole features so that old components can be replaced with new components and still match fit with the airframe includes the steps of adhering a bushing assembly into a fixture plate, rigidly attaching the fixture plate with the bushing assembly to the old component, heating the liquid metal above the liquid metal melting temperature such that the cylindrical drill bushing can move within the assembly, inserting an alignment pin within the cylindrical drill bushing such that the alignment pin is also inserted into an existing hole in the old component and the airframe, allowing the liquid metal to re-solidify; removing the alignment pin from the old component, replacing the old component with the new component, and using the re-solidified assembly as a drill guide for replacing holes in the new component.

A method of manufacturing a component includes additively manufacturing a crucible; directionally solidifying a metal material within the crucible; and removing the crucible to reveal the component. A component for a gas turbine engine includes a directionally solidified metal material component, the directionally solidified metal material component having been additively manufactured of a metal material concurrently with a core, the metal material having been remelted and directionally solidified.

A method of manufacturing a component includes additively manufacturing a crucible; directionally solidifying a metal material within the crucible; and removing the crucible to reveal the component. A component for a gas turbine engine includes a directionally solidified metal material component, the directionally solidified metal material component having been additively manufactured of a metal material concurrently with a core, the metal material having been remelted and directionally solidified.

Methods are provided for manufacturing a component. In one method, first metal material is cast into a first body. At least a portion of the first body is machined. Second metal material is cast onto at least the machined portion of the first body to form a monolithic second body. A first portion of the second body is formed by the first metal material, A second portion of the second body is formed by the second metal material. The second metal material is different from the first metal material.

Methods are provided for manufacturing a component. In one method, first metal material is cast into a first body. At least a portion of the first body is machined. Second metal material is cast onto at least the machined portion of the first body to form a monolithic second body. A first portion of the second body is formed by the first metal material, A second portion of the second body is formed by the second metal material. The second metal material is different from the first metal material.

Methods for performing in situ balancing of an internal rotating component of a gas turbine engine are provided. The method can include inserting a repair tool through an access port of the gas turbine engine with the repair tool including a tip end positioned within the gas turbine engine and a material supply end positioned outside the gas turbine engine. The tip end of the repair tool is positioned adjacent to a surface of the internal rotating component of the gas turbine engine. A new material is supplied from the material supply end of the repair tool to the tip end of the repair tool; and is expelling from the tip end of the repair tool in a direction of the surface of the rotating component such that the new material is added onto a portion of the rotating part.