Abstract: An automated method for restoring an end surface of a cylindrical component of a turbine engine by cutting a profile into the end surface is provided. A base of a cutting device is installed against an inner diameter of the cylindrical component. The base is the aligned to the end surface. A cutting head of the cutting device is positioned to a desired position to enable the cutting. A motor of the cutting device is activated to rotate the cutting head about a central axis of the cylindrical component to cut the end surface of the cylindrical component. A profile of the end surface is created by the cutting of the end surface via the motor. Upon activation of the motor, the cutting device is guided along a circumferential direction against the end surface. A system for cutting a profile into a surface of a cylindrical component is also provided.

Abstract: An automated method for restoring an end surface of a cylindrical component of a turbine engine by cutting a profile into the end surface is provided. A base of a cutting device is installed against an inner diameter of the cylindrical component. The base is the aligned to the end surface. A cutting head of the cutting device is positioned to a desired position to enable the cutting. A motor of the cutting device is activated to rotate the cutting head about a central axis of the cylindrical component to cut the end surface of the cylindrical component. A profile of the end surface is created by the cutting of the end surface via the motor. Upon activation of the motor, the cutting device is guided along a circumferential direction against the end surface. A system for cutting a profile into a surface of a cylindrical component is also provided.

Abstract: A gas turbine igniter includes an igniter rod disposed within a guide tube configured for travel between a hot-end region and a cold-end region and a cap connected to the guide tube, the cap defining an access passageway for the igniter rod. An attachment structure is provided for reducing the moment loading at the cold end of the igniter rod. The attachment structure has threaded outer surface configured to engage in a threaded connection with a threaded inner surface of the cap in an end portion of the cap that is proximate to the cold-end region, whereby the attachment structure is attachable to the end portion of the cap via the threaded connection. An inner surface of the attachment structure forms a guide surface for the igniter rod, at a reduced radial clearance with the igniter rod in comparison to the cap, proximate to the cold-end region.

Abstract: A turbine engine blade removal apparatus with a pair of opposed outwardly biased blocks are positioned proximal a blade root and corresponding rotor disc slot between opposed axial faces of the subject first rotor disc and an adjoining second rotor disc. The blocks are outwardly biased in abutting contact with first and second rotor disc axial faces, aligning an aperture of a guide bushing with an exposed axial face of the blade root, the guide bushing coupled to at least the first block. A punch is inserted in the guide bushing aperture so that a punch tip is in abutting relationship with the blade root axial face. An impact tool drives an opposite impact end of the punch, causing the punch to direct a relative driving force on the blade root, separating the blade root from the corresponding rotor disc slot.

Abstract: A process is provided for aligning a seal housing assembly with a casing of a gas turbine engine. The casing may comprise a plurality of connecting portions and the seal housing assembly may comprise a plurality of connecting sections. The process may comprise: providing an adjustment tool comprising: a main housing including a first bore and a threaded bore, a first bolt capable of extending through the first bore, and a second bolt capable of threadedly engaging the threaded bore. The process may further comprise mounting the adjustment tool to one of the seal housing assembly connecting sections via the first bolt and adjusting the position of the seal housing assembly relative to the casing by causing the second bolt to move.

Abstract: A method and apparatus for improved turbine bellyband rotor seal machining, installation and life are disclosed. A fixture is provided which can be temporarily attached to the turbine disks in a position straddling the gap between the disks, without destacking the turbine rotor. The fixture accepts power tools including a drill and a mill, and positions the power tools to drill and grind a rectangular slot into the disks, where the slot has the exact size and shape needed to receive an anti-rotation block which is integral to the replacement bellyband. Measuring tools are also provided which enable precise location of each of the four slots which must be machined in the disks. The resulting slots have a uniform size and shape, and are equally spaced around the circumference of the disk, thereby facilitating installation of the service bellyband from four identical segments.

Abstract: A method and apparatus for improved turbine bellyband rotor seal machining, installation and life are disclosed. A fixture is provided which can be temporarily attached to the turbine disks in a position straddling the gap between the disks, without destacking the turbine rotor. The fixture accepts power tools including a drill and a mill, and positions the power tools to drill and grind a rectangular slot into the disks, where the slot has the exact size and shape needed to receive an anti-rotation block which is integral to the replacement bellyband. Measuring tools are also provided which enable precise location of each of the four slots which must be machined in the disks. The resulting slots have a uniform size and shape, and are equally spaced around the circumference of the disk, thereby facilitating installation of the service bellyband from four identical segments.

Abstract: A turbine engine blade removal apparatus with a pair of opposed outwardly biased blocks are positioned proximal a blade root and corresponding rotor disc slot between opposed axial faces of the subject first rotor disc and an adjoining second rotor disc. The blocks are outwardly biased in abutting contact with first and second rotor disc axial faces, aligning an aperture of a guide bushing with an exposed axial face of the blade root, the guide bushing coupled to at least the first block. A punch is inserted in the guide bushing aperture so that a punch tip is in abutting relationship with the blade root axial face. An impact tool drives an opposite impact end of the punch, causing the punch to direct a relative driving force on the blade root, separating the blade root from the corresponding rotor disc slot.

Abstract: A process is provided for aligning a seal housing assembly with a casing of a gas turbine engine. The casing may comprise a plurality of connecting portions and the seal housing assembly may comprise a plurality of connecting sections. The process may comprise: providing an adjustment tool comprising: a main housing including a first bore and a threaded bore, a first bolt capable of extending through the first bore, and a second bolt capable of threadedly engaging the threaded bore. The process may further comprise mounting the adjustment tool to one of the seal housing assembly connecting sections via the first bolt and adjusting the position of the seal housing assembly relative to the casing by causing the second bolt to move.

Abstract: A gas turbine igniter includes an igniter rod disposed within a guide tube configured for travel between a hot-end region and a cold-end region and a cap connected to the guide tube, the cap defining an access passageway for the igniter rod. An attachment structure is provided for reducing the moment loading at the cold end of the igniter rod. The attachment structure has threaded outer surface configured to engage in a threaded connection with a threaded inner surface of the cap in an end portion of the cap that is proximate to the cold-end region, whereby the attachment structure is attachable to the end portion of the cap via the threaded connection. An inner surface of the attachment structure forms a guide surface for the igniter rod, at a reduced radial clearance with the igniter rod in comparison to the cap, proximate to the cold-end region.

Abstract: A system and method for repairing turbine vane attachment systems in a turbine engine. In at least one embodiment, the invention may be directed to a system and method for repairing wear on a diaphragm hook fit configured to attach diaphragm airfoils, such as stationary turbine vanes, to a combustion turbine case. The restoration system may be formed from a carriage assembly having an assortment of material processing implements usable to build up material in the worn locations of the turbine vane attachment system to reestablish a diaphragm hook fit within the specified tolerances. The restoration system may be configured so that the restoration process may occur without removing a rotor assembly, which can reduce the repair time by about two weeks. Thus, use of the restoration system can result in a significant time and cost savings.

Abstract: A system and method for repairing turbine vane attachment systems in a turbine engine. In at least one embodiment, the invention may be directed to a system and method for repairing wear on a diaphragm hook fit configured to attach diaphragm airfoils, such as stationary turbine vanes, to a combustion turbine case. The restoration system may be formed from a carriage assembly having an assortment of material processing implements usable to build up material in the worn locations of the turbine vane attachment system to reestablish a diaphragm hook fit within the specified tolerances. The restoration system may be configured so that the restoration process may occur without removing a rotor assembly, which can reduce the repair time by about two weeks. Thus, use of the restoration system can result in a significant time and cost savings.

Abstract: A system and method for repairing turbine vane attachment systems in a turbine engine. In at least one embodiment, the invention may be directed to a system and method for repairing wear on a diaphragm hook fit configured to attach diaphragm airfoils, such as stationary turbine vanes, to a combustion turbine case. The restoration system may be formed from a carriage assembly having an assortment of material processing implements usable to build up material in the worn locations of the turbine vane attachment system to reestablish a diaphragm hook fit within the specified tolerances. The restoration system may be configured so that the restoration process may occur without removing a rotor assembly, which can reduce the repair time by about two weeks. Thus, use of the restoration system can result in a significant time and cost savings.

Abstract: A jig is structured to guide a grinder along the inner surface of the base or cover of a combustion turbine. The jig includes a base having a bottom surface with a plurality of rollers arranged in substantially the same radius as the portion of the casing being repaired. Side rollers locate the base horizontally during movement. A top platform may restrain the base vertically by supporting a pivot block that bears against the rotor of the turbine. The grinder may be moved vertically or horizontally with respect to the base upon which it is secured.