Abstract: A milling device for machining a slot into an inner surface of a casing for a gas turbine engine. The milling device includes a frame assembly including multiple structural guides configured to engage structural features on the inner surface of the casing to maintain an axial position of the milling device relative to a longitudinal axis of the casing. The milling device also includes a milling cutter coupled to the frame assembly. The milling device is configured to be displaced in a circumferential direction relative to the longitudinal axis to machine the slot, via the milling cutter, along the inner surface of the casing in the circumferential direction.

Abstract: A milling device for machining a slot into an inner surface of a casing for a gas turbine engine. The milling device includes a frame assembly including multiple structural guides configured to engage structural features on the inner surface of the casing to maintain an axial position of the milling device relative to a longitudinal axis of the casing. The milling device also includes a milling cutter coupled to the frame assembly. The milling device is configured to be displaced in a circumferential direction relative to the longitudinal axis to machine the slot, via the milling cutter, along the inner surface of the casing in the circumferential direction.

Abstract: A milling device for machining a slot into an inner surface of a casing for a gas turbine engine. The milling device includes a frame assembly including multiple structural guides configured to engage structural features on the inner surface of the casing to maintain an axial position of the milling device relative to a longitudinal axis of the casing. The milling device also includes a milling cutter coupled to the frame assembly. The milling device is configured to be displaced in a circumferential direction relative to the longitudinal axis to machine the slot, via the milling cutter, along the inner surface of the casing in the circumferential direction.

Abstract: A milling device for machining a slot into an inner surface of a casing for a gas turbine engine. The milling device includes a frame assembly including multiple structural guides configured to engage structural features on the inner surface of the casing to maintain an axial position of the milling device relative to a longitudinal axis of the casing. The milling device also includes a milling cutter coupled to the frame assembly. The milling device is configured to be displaced in a circumferential direction relative to the longitudinal axis to machine the slot, via the milling cutter, along the inner surface of the casing in the circumferential direction.

Abstract: The present application provides a tool for cleaning a groove of a turbine rotor disk. The tool may include a pair of guides spaced apart from one another in a direction of a longitudinal axis of the tool, and a number of cleaning sheets positioned between the guides in the direction of the longitudinal axis of the tool. At least a portion of each guide may have a cross-sectional profile corresponding to a cross-sectional profile of the groove, and at least a portion of each cleaning sheet may have a cross-sectional profile corresponding to the cross-sectional profile of the groove. The present application further provides a method for cleaning a groove of a turbine rotor disk, and a tool system for cleaning a groove of a turbine rotor disk.

Abstract: Aspects of the disclosure include a removable support for additive manufacture and methods and code for manufacturing and removing the same. A removable support for a laser-sintered component having at least one surface to connect to may include a support body, a first set of connectors, and a second set of connectors. The support body may have a first wing and a second wing, each with a distal surface and a lateral midline bisecting the distal surface. Each set of connectors may project from the distal surface on one side of the lateral midline of their respective wings to connect to the surface of the component while the distal surface also defines a connector-free portion on the other side of the lateral midline.

Abstract: Aspects of the disclosure include a machine and system for support removal and a laser-sintered component compatible with same. A laser-sintered component may have a component surface and at least one laser-sintered support extending from the component surface. A press may move a cutting surface along a cutting path adjacent to the component surface. The cutting surface has a shape complementary to the component surface and at least one cutting edge positioned to separate at least one laser-sintered support from the component surface as the cutting surface moves along the cutting path.

Abstract: The present application provides a tool for cleaning a groove of a turbine rotor disk. The tool may include a pair of guides spaced apart from one another in a direction of a longitudinal axis of the tool, and a number of cleaning sheets positioned between the guides in the direction of the longitudinal axis of the tool. At least a portion of each guide may have a cross-sectional profile corresponding to a cross-sectional profile of the groove, and at least a portion of each cleaning sheet may have a cross-sectional profile corresponding to the cross-sectional profile of the groove. The present application further provides a method for cleaning a groove of a turbine rotor disk, and a tool system for cleaning a groove of a turbine rotor disk.

Abstract: Aspects of the disclosure include a removable support for additive manufacture and methods and code for manufacturing and removing the same. A removable support for a laser-sintered component having at least one surface to connect to may include a support body, a first set of connectors, and a second set of connectors. The support body may have a first wing and a second wing, each with a distal surface and a lateral midline bisecting the distal surface. Each set of connectors may project from the distal surface on one side of the lateral midline of their respective wings to connect to the surface of the component while the distal surface also defines a connector-free portion on the other side of the lateral midline.

Abstract: Aspects of the disclosure include a machine and system for support removal and a laser-sintered component compatible with same. A laser-sintered component may have a component surface and at least one laser-sintered support extending from the component surface. A press may move a cutting surface along a cutting path adjacent to the component surface. The cutting surface has a shape complementary to the component surface and at least one cutting edge positioned to separate at least one laser-sintered support from the component surface as the cutting surface moves along the cutting path.

Abstract: Aspects of the disclosure include removable support packages for additive manufacture, in addition methods and code for manufacturing and removing the same. A removable support package for a laser-sintered component according to the present disclosure may include: a structure having opposing interior sidewalls, the opposing interior sidewalls defining a hollow interior of the structure; a plurality of supports extending between the opposing interior sidewalls of the structure; a first rod joining the plurality of supports at a first end proximal to one interior sidewall of the structure; and a second rod joining the plurality of supports at a second end proximal to another opposing interior sidewall of the structure.

Abstract: A tool for measuring geometrical parameters of a vane or a blade of a turbomachine, particularly for measuring a distance between the tip of the vane or blade and a reference plane is provided. The tool includes a first guiding plate and a second guiding plate. The first guiding plate and the second guiding plate are spaced apart from each other in a defined position by means of at least two spacers. Each of the first guiding plate and the second guiding plate is equipped with a first through hole and one or more second through holes. The first through hole is designed to insert through an airfoil of said vane or blade. Each of the second through holes is designed to receive a length measuring tool, e.g. a depth gauge.

Abstract: A bolt adjustment device having a body, a clamping mechanism and an attachment point. The body extends in a longitudinal direction from a first end to a second end, the body having a cavity extending into the body in the longitudinal direction from the first end. The cavity can accommodate a thread during use of the bolt adjustment device. A step in the cavity is configured and arranged to engage with a nut when in use. A torque imparted on the attachment point will impart a torque to the bolt adjustment device. The clamping mechanism is attached to the attachment point such that the clamping mechanism clamps the nut in the cavity when torque is imparted on the clamping device.

Abstract: A tool for measuring geometrical parameters of a vane or a blade of a turbomachine, particularly for measuring a distance between the tip of the vane or blade and a reference plane is provided. The tool includes a first guiding plate and a second guiding plate. The first guiding plate and the second guiding plate are spaced apart from each other in a defined position by means of at least two spacers. Each of the first guiding plate and the second guiding plate is equipped with a first through hole and one or more second through holes. The first through hole is designed to insert through an airfoil of said vane or blade. Each of the second through holes is designed to receive a length measuring tool, e.g. a depth gauge.