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: An exemplary pullable drawer is arranged for removably protruding in a radial direction into an outer housing of a turbine, in order to make mechanical contact with an inner carrier being concentrically arranged within the outer housing. The pullable drawer has an essentially cylindrical body, which extends along a longitudinal drawer axis. A mechanical decoupling is provided, as the pullable drawer is divided along the longitudinal drawer axis into at least separate first and second parts. The first and second parts are coupled with each other by means of a releasable mechanical joint.

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.

Abstract: The invention is related to a pullable drawer for removably protruding in a radial direction into an outer housing of a turbine, in order to make mechanical contact with an inner carrier being concentrically arranged within said outer housing. The pullable drawer has an essentially cylindrical body, which extends along a longitudinal drawer axis. A mechanical decoupling is provided, as the pullable drawer is divided along said longitudinal drawer axis into at least separate first and second parts. The first and second parts are coupled with each other by means of a releasable mechanical joint.

Abstract: A leaf seal for sealing a shaft rotating about an axis, in particular in a gas turbine, includes a multiplicity of spaced-apart leaves (26) which are arranged in a concentric circle around the axis and are fixed in their position by welded connections produced by electron beam welding, the leaves (26), with their surfaces, being oriented essentially parallel to the axis. The welded connections of the leaves are improved by the leaves (26) being designed in such a way and being arranged in the leaf seal in such a way that they abut against one another at the side edges directly or via intermediate spacers (27) along at least one contact line (36) extending over a plurality of leaves (26), and by the welded connections being designed as welds directed along the at least one contact line (36) and oriented in axial direction.

Abstract: A lamellar seal for sealing a shaft which rotates around an axis, especially in a gas turbine, includes a multiplicity of lamella (13) which are spaced one beneath the other, arranged in a concentric circle around the axis, and fixed in their position, wherein the lamellae (13) by their surfaces are oriented essentially parallel to the axis. The lamellar seal is improved by the fact that the lamellae (13) have formed-on structures (19, 20, 21) in each case for positioning and retaining the lamellae (13) in the lamellar seal (12), which include one or more laterally projecting support arms (19, 20, 21) which engage in complementarily formed recesses (25, 26) of the end plates (15, 16).

Abstract: A lamellar seal for sealing a shaft which rotates around an axis, especially in a gas turbine, includes a multiplicity of lamella (13) which are spaced one beneath the other, arranged in a concentric circle around the axis, and fixed in their position, wherein the lamellae (13) by their surfaces are oriented essentially parallel to the axis. The lamellar seal is improved by the fact that the lamellae (13) have formed-on structures (19, 20, 21) in each case for positioning and retaining the lamellae (13) in the lamellar seal (12), which include one or more laterally projecting support arms (19, 20, 21) which engage in complementarily formed recesses (25, 26) of the end plates (15, 16).

Abstract: A leaf seal for sealing a shaft rotating about an axis, in particular in a gas turbine, includes a multiplicity of spaced-apart leaves (26) which are arranged in a concentric circle around the axis and are fixed in their position by welded connections produced by electron beam welding, the leaves (26), with their surfaces, being oriented essentially parallel to the axis. The welded connections of the leaves are improved by the leaves (26) being designed in such a way and being arranged in the leaf seal in such a way that they abut against one another at the side edges directly or via intermediate spacers (27) along at least one contact line (36) extending over a plurality of leaves (26), and by the welded connections being designed as welds directed along the at least one contact line (36) and oriented in axial direction.

Abstract: A support (1) for a reflective target to be mounted on a turbine casing, which is used in casing bending measurements. The support (1) comprises a tube (2), which was chosen to ensure a thermal expansion coefficient near zero at the operating temperatures of the casing. The tube (2) is located at one end in a steel holder (3). In the middle of the tube (2) is arranged a metal rod (9), which is fixed to the holder (3). At the opposite end of the tube (2) is an insert (7), which has an apertures through which passes the metal rod (9). Within the insert (7) the metal rod (9) is screw threaded so it can be turned to provide always enough tension at all operating temperatures and the metal tube (9) is held tight, secure, and has minimal vibration.

Abstract: A support (1) for a reflective target to be mounted on a turbine casing, which is used in casing bending measurements. The support (1) comprises a tube (2), which was chosen to ensure a thermal expansion coefficient near zero at the operating temperatures of the casing. The tube (2) is located at one end in a steel holder (3). In the middle of the tube (2) is arranged a metal rod (9), which is fixed to the holder (3). At the opposite end of the tube (2) is an insert (7), which has an apertures through which passes the metal rod (9). Within the insert (7) the metal rod (9) is screw threaded so it can be turned to provide always enough tension at all operating temperatures and the metal tube (9) is held tight, secure, and has minimal vibration.

Abstract: Upper and lower mirror image die plates are resiliently supported and have predetermined displacement values for forming vortex generators and foldline crease channels without compressive deformation in a porous sintered metal fiber sheet material. Cutters and ridges coupled to the upper and lower die plates form the respective vortex generators and channels. The sheet of so formed material is then placed in an apparatus for bending the sheet at the foldline channels to corrugate the sheet without deformation of the sheet material between the corrugation bends. Fingers align with and engage the channels. The fingers are on plates that are ramped closer together simultaneously while the fingers on two mirror image coplanar sets of plates displace toward each other as the sheet material is folded. Pins on a pair of rotating levers engage each of the finger plates of the two sets for relatively horizontally displacing the plates and corresponding fingers as they are ramped together vertically.

Abstract: In a method for the firm bonding at elevated temperatures of thin, large-area wafers of different thermal expansion the deformations of the laminar bond occurring later during cooling are at least partially compensated by an appropriate pre-deformation in the opposite direction. An apparatus for conducting the method uses the different thermal expansion of a housing (1) and a ring-shaped thermal expansion element (3) to produce the pre-deformation.