Methods and apparatus for forming an aperture in a composite component are provided. For example, a method for forming an aperture in a ceramic matrix composite (CMC) component comprises, based on a final dimension of the aperture, selecting a tool having a tool size and a cutting surface; selecting an angle at which to cut the component with the tool; cutting a back surface of the component with the tool, the cutting surface positioned at the angle; repositioning the tool relative to the component; and cutting the aperture through to its final dimension. The tool may be a core drill with a diameter within a range of 60% to 90% of the aperture final dimension. The angle may be within a range of 10° to 60° with respect to the back surface. The aperture may be cut through to its final dimension from a front surface of the component.

A cutting system for removing an excess material along a length of a channel constructed using an additive manufacturing process is disclosed. In various embodiments, the cutting system includes a cutter head; a cutter blade attached to the cutter head; a drive cable configured to rotate the cutter head; and a cutter base attached to the cutter head and having a cutter base outer surface configured to contact an internal surface within the channel to guide the cutter blade against the excess material.

Apparatus for machining a component of a gas turbine engine, the apparatus including: a flexible pipe having a first end and a second end and defining a conduit for receiving a fluid; one or more first actuators arranged to enable the first end of the flexible pipe to be re-positioned relative to the second end of the flexible pipe; a turbine positioned adjacent to the first end of the flexible pipe, the turbine being arranged to receive fluid from the conduit of the flexible pipe; and a tool head coupled to the first end of the flexible pipe, the tool head including: a fastener arranged to fasten to a tool and to receive torque from the turbine.

A device for localizing a position on a part includes a support to receive the part, a bushing movably mounted with respect to the support, a removable localization member to be inserted into the bushing, and a blocking device to fix the bushing with respect to the support and to maintain it in position.

A method comprises the steps of providing a tool over a collar secured to a stud on a gas turbine engine system. The collet is driven to rotate and remove the collar from the stud. A tool for removing collars from studs has a driver with a housing receiving a piston. A spring drives the piston, and the housing also has a hydraulic fluid supply opening for selectively receiving a hydraulic fluid to move the piston in opposition to a force from the spring. Collet fingers are movable between a released position and a secured position when a supply of hydraulic fluid is supplied into the housing.

Method and equipment for repairing the roots of wind turbine blades, by drilling on the root of the blade, and through the ring thereof, radial bore holes located in positions that radially match the axial threaded blind holes of the ring; grinding and drilling the axial threaded blind holes to remove the thread, and to achieve the extension of the ground axial holes until they reach the matching radial bore hole; introducing, into each radial bore hole, a pin provided with a threaded diametral passage aligned with a threaded axial hole of the ring; screwing bolts into the axial threaded blind holes and threaded diametral passages, for fastening the blade to the hub of the wind turbine. The equipment has a support that can be fastened to the reinforcement ring and a head for carrying radial and axial drilling tools.

A gas turbine part with a cooling hole, is fabricated by first forming a model of a wall of a gas turbine part. The wall is defined by first and second surfaces, the first surface having an aperture indentation possessing a complex geometry and extending into but not all the way through the wall of the gas turbine part. A mold of the wall of the gas turbine part is formed using the model and is used to cast the wall of the gas turbine part by lost-material casting. A passage is drilled through the resulting casting. This passage extends from the aperture indentation in the first surface through to the second surface.

Methods and apparatus for forming an aperture in a composite component are provided. For example, a method for forming an aperture in a ceramic matrix composite (CMC) component comprises, based on a final dimension of the aperture, selecting a tool having a tool size and a cutting surface; selecting an angle at which to cut the component with the tool; cutting a back surface of the component with the tool, the cutting surface positioned at the angle; repositioning the tool relative to the component; and cutting the aperture through to its final dimension. The tool may be a core drill with a diameter within a range of 60% to 90% of the aperture final dimension. The angle may be within a range of 10 to 60 with respect to the back surface. The aperture may be cut through to its final dimension from a front surface of the component.

Machining tool for internal machining of a shaft (2) with an inner bore (3), such as an aircraft engine turbine shaft (fan mid shaft). The machining tool has an external boring bar (6) support device (5), and a boring bar (6) having a diameter smaller than a smallest opening on one side (4) of the inner bore (3) of the shaft (2). The boring bar (6) has a radially extensible cutting insert (7), and an end part (6b) of the boring bar (6) is rotatably connected to a main part (6a) of the boring bar (6). The end part (6b) is provided with one or more radially moveable guiding pads (8).

A cutting system for removing an excess material along a length of a channel constructed using an additive manufacturing process is disclosed. In various embodiments, the cutting system includes a cutter head; a cutter blade attached to the cutter head; a drive cable configured to rotate the cutter head; and a cutter base attached to the cutter head and having a cutter base outer surface configured to contact an internal surface within the channel to guide the cutter blade against the excess material.