Abstract:
Various embodiments include approaches for installing a flow sleeve relative to a gas turbine transition piece. Some embodiments include an apparatus for coupling a gas turbine transition piece with a flow sleeve, the installation apparatus having: a radially inner ring; a plurality of expander segments extending radially outward from the radially inner ring, the plurality of expander segments each having an axially ramped segment sized to gradually expand the flow sleeve to couple with the gas turbine transition piece as the flow sleeve is moved along the plurality of expander segments; and a circumferentially disposed space separating each pair of adjacent expander segments in the plurality of expander segments.
Abstract:
A turbomachine rotor blade milling machine system includes a fixture having a body including first and second opposing surfaces and a slot. The fixture is configured and disposed to connect with first and second rotor blade sections mounted in a rotor wheel. A mounting system includes at least one mounting element coupled to one of the first and second opposing surfaces of the body at the slot. A milling machine is coupled to the one of the first and second opposing surfaces through the at least one mounting element. The milling machine includes a cutter and is configured and disposed to form an opening extending axially through a dovetail portion of a third rotor blade section arranged between the first and second rotor blade sections.
Abstract:
An adjustable working platform for a curved surface includes a support member configured to be inserted into a hole in the curved surface. An adjustable surface is configured for supporting a load, and the adjustable surface is configured to rotate and lock in multiple positions. An anti-rotation arm is connected to the support member, and the anti-rotation arm includes an adjustable section configured to engage an axial facing portion of the curved surface.
Abstract:
An apparatus and method for a more time efficient measurement of backlash in one or more variable guide vanes of a gas turbine system are provided. A mounting structure, with an indicator attached thereto, may be provided. Further, a guide structure may be provided to allow the mounting structure to be moved adjacent to two or more variable guide vanes without moving the guide structure.
Abstract:
An apparatus for cleaning an inner surface of a slot includes a first block segment that has an outer perimeter that conforms to and fits inside the inner surface of the slot. A first cleaning pad is connected to the first block segment and extends beyond at least a portion of the outer perimeter of the first block segment.
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 turbomachine rotor blade milling machine system includes a fixture having a body including first and second opposing surfaces and a slot. The fixture is configured and disposed to connect with first and second rotor blade sections mounted in a rotor wheel. A mounting system includes at least one mounting element coupled to one of the first and second opposing surfaces of the body at the slot. A milling machine is coupled to the one of the first and second opposing surfaces through the at least one mounting element. The milling machine includes a cutter and is configured and disposed to form an opening extending axially through a dovetail portion of a third rotor blade section arranged between the first and second rotor blade sections.
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:
An apparatus and system for assembling a combustor comprises a push bar including a first end portion that is laterally opposed from a second end portion. A first alignment block and a second alignment block are adjustably coupled to the push bar. A first threaded rod extends through the push bar proximate to the first end portion and a second threaded rod extends through the push bar proximate to the second end portion. The first alignment block and the second alignment block extend outwardly from an aft side of the push bar and are positioned between the first threaded rod and the second threaded rod. The installation tool includes a first nut and a second nut for applying axial force to the push bar.
Abstract:
A tool for drilling, tapping, and back spot facing at least one hole in a turbomachine includes a servo motor cutting device configured for use with a cutting tool. A drill unit skid is adapted to engage a hook fit slot in a case of the turbomachine, and for supporting the servo motor cutting device, and the drill unit skid including hook fit slides. The hook fit slides guide the drill unit skid along the hook fit slot and act as a stop in a radial direction with respect to the turbomachine. A laser positioning device detects the position of the cutting tool. A micro switch stops the servo motor cutting device when the micro switch activates. The servo motor cutting device rotates the cutting tool to create the hole, while a rotor of the turbomachine is left in place during drilling, tapping and back spot facing.