Abstract: A cooling bore guide for reaming an enlarged portion into a cooling bore of a rotor. The cooling bore guide may include a cutter guide for insertion into the cooling bore and a guide lock for insertion into an adjacent cooling bore.

Abstract: The present application provides a bump check tool for determining a clearance between a shim of a thrust bearing and a rotor flange of a rotor shaft within a casing of a gas turbine engine. The bump check tool includes a hydraulic cylinder, a connection plate attached to the hydraulic cylinder and positioned about the rotor shaft and a support frame supporting the hydraulic cylinder and attached to the casing. The hydraulic cylinder drives the connection plate and the rotor shaft to determine the clearance between the shim of the thrust bearing and the rotor flange of the rotor shaft.

Abstract: Various embodiments include methods for performing maintenance on a gas turbine bearing area. In some cases, a method includes: separating sections of an inlet bellmouth of the gas turbine without removing the sections of the inlet bellmouth from the gas turbine; removing a housing from over a bearing of the gas turbine; mounting a bearing maintenance apparatus adjacent the inlet bellmouth and the bearing; and performing maintenance on the bearing area while the sections of the inlet bellmouth remain separated.

Abstract: Embodiments of the disclosure include a method to create a three-dimensional (3D) tool frame for a robot. The method includes identifying a reference point on a calibration grid using a robotic vision system, such as a camera or laser. The identified reference point is used to create a user frame coordinate system with an origin at the identified reference point. The identified reference point being equal to a field of view origin created by a 3D scanner. Being at the specific location where the field of view origin is created during calibration, a 3D tool frame is created based on user frame location. The 3D tool frame indicates the location and orientation of the 3D scanner in the field of view coordinate system.

Abstract: Various embodiments include methods for performing maintenance on a gas turbine bearing area. In some cases, a method includes: separating sections of an inlet bellmouth of the gas turbine without removing the sections of the inlet bellmouth from the gas turbine; removing a housing from over a bearing of the gas turbine; mounting a bearing maintenance apparatus adjacent the inlet bellmouth and the bearing; and performing maintenance on the bearing area while the sections of the inlet bellmouth remain separated.

Abstract: Various embodiments include apparatuses for performing maintenance on a gas turbine bearing area, along with related methods. One apparatus can include: a set of rails sized to couple with the gas turbine and rest coaxially with a bearing adjacent the gas turbine, the set of rails for supporting a portion of a housing of the bearing; a first platform spanning between the set of rails; a lifting device coupled to the first platform for engaging an inlet bellmouth of the gas turbine; and a second platform suspended from the set of rails sized to accommodate an operator.

Abstract: A system for use in performing maintenance on a turbine rotor. The system includes a rotor mount configured to receive the turbine rotor, a robotic device, a visual inspection device removably coupleable to the robotic device, and a computing device. The computing device is configured to direct the robotic device to evaluate, with the visual inspection device, the turbine rotor at different circumferential locations thereof to obtain rotor axis data, determine a centerline of the turbine rotor based on the rotor axis data, generate a coordinate system including the centerline of the turbine rotor, direct the robotic device to evaluate, with the visual inspection device, each blade on at least one stage of the turbine rotor to obtain blade position data relative to the centerline, and populate the coordinate system with the blade position data.

Abstract: An alignment apparatus for aligning inlet guide vanes in a turbine having a turbine axis includes a tool body, a positioning block secured to the tool body, and a plurality of alignment pieces secured to the tool body. The positioning block may be affixed to the tool body such that when the positioning block is engaged with a leading edge of one of the inlet guide vanes, at least a portion of the alignment pieces is parallel to the turbine axis. The alignment pieces may be manually displaceable from the OFF position to the ON position into engagement with the inlet guide vanes to align one or more of the inlet guide vanes.

Abstract: An apparatus and method for servicing a combustion liner in a combustion case of a turbine is provided. The apparatus includes an elongated bar having a handle at one end and a force applying member at an opposing end of the elongated bar. An attachment member is configured for attachment to a flange of the combustion case. The attachment member is also configured for pivotal attachment to the elongated bar. The apparatus is configured to apply a radially outward force on a downstream portion of the combustion liner when a radially inward force is applied to the handle.

Abstract: Various embodiments include apparatuses for performing maintenance on a gas turbine bearing area, along with related methods. One apparatus can include: a set of rails sized to couple with the gas turbine and rest coaxially with a bearing adjacent the gas turbine, the set of rails for supporting a portion of a housing of the bearing; a first platform spanning between the set of rails; a lifting device coupled to the first platform for engaging an inlet bellmouth of the gas turbine; and a second platform suspended from the set of rails sized to accommodate an operator.

Abstract: An alignment apparatus for aligning inlet guide vanes in a turbine having a turbine axis includes a tool body, a positioning block secured to the tool body, and a plurality of alignment pieces secured to the tool body. The positioning block may be affixed to the tool body such that when the positioning block is engaged with a leading edge of one of the inlet guide vanes, at least a portion of the alignment pieces is parallel to the turbine axis. The alignment pieces may be manually displaceable from the OFF position to the ON position into engagement with the inlet guide vanes to align one or more of the inlet guide vanes.

Abstract: A rotor turning system for turning a rotor is provided. The system may include a rotary driver including a rotating drive shaft. A removable rotor grasping element is configured to frictionally grasp at least a portion of an exterior circumference of a portion of the rotor. A drive linkage couples the rotating drive shaft to the rotor grasping element to impart a torque to the rotor with the rotor grasping element to turn the rotor. A rotor grasping element is also provided for grasping a substantially smooth exterior surface of a rotor to allow for turning of the rotor. A related method is also provided.

Abstract: A tool for removing a fastener head from a fastener includes a body that includes an alignment surface configured to couple substantially flush against a structural surface proximate the fastener head. A blade coupled to the body includes a tip configured to sever the fastener head from the fastener as the blade is moved in a first direction generally parallel to the alignment surface from a first blade position to a second blade position. The tool also includes a force transfer member coupled to the body for movement parallel to a longitudinal axis of the force transfer member. The longitudinal axis is oriented at an acute angle with respect to the first direction. The force transfer member is configured to move the blade from the first blade position to the second blade position in response to an impulse received by the force transfer member.

Abstract: A rotor turning system for turning a rotor is provided. The system may include a rotary driver including a rotating drive shaft. A removable rotor grasping element is configured to frictionally grasp at least a portion of an exterior circumference of a portion of the rotor. A drive linkage couples the rotating drive shaft to the rotor grasping element to impart a torque to the rotor with the rotor grasping element to turn the rotor. A rotor grasping element is also provided for grasping a substantially smooth exterior surface of a rotor to allow for turning of the rotor. A related method is also provided.

Abstract: A turbine shroud block removal apparatus. In one embodiment, the apparatus includes a first base plate including a first armature. The first base plate may be releasably coupled to a first shroud block. The apparatus also may also include a second base plate including a second armature. The second base plate may be releasably coupled to a second shroud block positioned adjacent the first shroud block. Additionally, the apparatus may include an actuator coupled to the first armature of the first base plate and the second armature of the second base plate. The actuator may change a distance between the first shroud block and the second shroud block.

Abstract: A tool for removing a fastener head from a fastener includes a body that includes an alignment surface configured to couple substantially flush against a structural surface proximate the fastener head. A blade coupled to the body includes a tip configured to sever the fastener head from the fastener as the blade is moved in a first direction generally parallel to the alignment surface from a first blade position to a second blade position. The tool also includes a force transfer member coupled to the body for movement parallel to a longitudinal axis of the force transfer member. The longitudinal axis is oriented at an acute angle with respect to the first direction. The force transfer member is configured to move the blade from the first blade position to the second blade position in response to an impulse received by the force transfer member.

Abstract: An apparatus and method for servicing a combustion liner in a combustion case of a turbine is provided. The apparatus includes an elongated bar having a handle at one end and a force applying member at an opposing end of the elongated bar. An attachment member is configured for attachment to a flange of the combustion case. The attachment member is also configured for pivotal attachment to the elongated bar. The apparatus is configured to apply a radially outward force on a downstream portion of the combustion liner when a radially inward force is applied to the handle.

Abstract: A turbine shroud block removal apparatus. In one embodiment, the apparatus includes a first base plate including a first armature. The first base plate may be releasably coupled to a first shroud block. The apparatus also may also include a second base plate including a second armature. The second base plate may be releasably coupled to a second shroud block positioned adjacent the first shroud block. Additionally, the apparatus may include an actuator coupled to the first armature of the first base plate and the second armature of the second base plate. The actuator may change a distance between the first shroud block and the second shroud block.