Abstract: A shipping fixture for a turbine lower casing includes a frame having a substantially rectangular shape including a pair of elongated, laterally-spaced side beams and a pair of transverse end beams. A first lateral support structure extends between the side beams at a first location corresponding to a first vertically-oriented joint between the turbine compressor casing section and the turbine combustor casing section; and a second lateral support structure includes support blocks mounted on the side beams at a second location corresponding to a second vertically-oriented joint between the turbine combustor casing section and the turbine stage casing section.

Abstract: A rotor of a turbomachine is provided. The rotor includes at least first and second rotor portions and at least first and second blades. The first and second rotor portions are configured to rotate about an axis. The first and second rotor portions have first and second rim portions, respectively, which are spaced a predetermined distance apart from one another and have a perimetrical slot therebetween. The first and second rim portions have first and second dovetail slots, respectively, extending therethrough communicating with the perimetrical slot. The first and second blades have first and second dovetail portions, respectively. The first dovetail portion is disposed in one of the first and second dovetail slots, and the second dovetail portion is disposed in the other of the first and second dovetail slots. The perimetrical slot has a sufficient size to pass the first and second blades therethrough when the first and second blades are removed from the rotor.

Abstract: A system and a method to supply a coolant to a turbine bucket of a turbine. The system includes an extraction system configured to extract air from a main compressor airflow, a supply circuit, at least a part of which is disposed at an exterior of the gas turbine, coupled to the extraction system and configured to transport the extracted air, as an ingredient of the coolant, from the extraction system to a coolant insertion region, and a cooling system, disposed proximate to the coolant insertion region of the gas turbine and coupled to the supply circuit at a position on-board the gas turbine, the cooling system being configured to supply the turbine bucket with the coolant, including the extracted air.

Abstract: A cooling system for a turbine includes a blower configured to generate a cooling gas flow to be passed through a rotor cavity of the turbine; piping configured to deliver the cooling gas flow to the turbine; and at least one valve configured to control the cooling gas flow. The piping is operatively connected to the rotor of the turbine. A method of cooling a turbine includes generating a cooling gas flow with a blower to be passed through a rotor cavity of the turbine; and delivering the cooling gas flow to the turbine.

Abstract: A cooling system for a turbine includes a blower configured to generate a cooling gas flow to be passed through a rotor cavity of the turbine; piping configured to deliver the cooling gas flow to the turbine; and at least one valve configured to control the cooling gas flow. The piping is operatively connected to the rotor of the turbine. A method of cooling a turbine includes generating a cooling gas flow with a blower to be passed through a rotor cavity of the turbine; and delivering the cooling gas flow to the turbine.

Abstract: A system and a method to supply a coolant to a turbine bucket of a turbine. The system includes an extraction system configured to extract air from a main compressor airflow, a supply circuit, at least a part of which is disposed at an exterior of the gas turbine, coupled to the extraction system and configured to transport the extracted air, as an ingredient of the coolant, from the extraction system to a coolant insertion region, and a cooling system, disposed proximate to the coolant insertion region of the gas turbine and coupled to the supply circuit at a position on-board the gas turbine, the cooling system being configured to supply the turbine bucket with the coolant, including the extracted air.

Abstract: A rotor of a turbomachine is provided. The rotor includes at least first and second rotor portions and at least first and second blades. The first and second rotor portions are configured to rotate about an axis. The first and second rotor portions have first and second rim portions, respectively, which are spaced a predetermined distance apart from one another and have a perimetrical slot therebetween. The first and second rim portions have first and second dovetail slots, respectively, extending therethrough communicating with the perimetrical slot. The first and second blades have first and second dovetail portions, respectively. The first dovetail portion is disposed in one of the first and second dovetail slots, and the second dovetail portion is disposed in the other of the first and second dovetail slots. The perimetrical slot has a sufficient size to pass the first and second blades therethrough when the first and second blades are removed from the rotor.

Abstract: Stacked wheels of the rotor of a rotary machine are axially coupled to one another by tie bolt assemblies. Each tie bolt assembly includes a stud having forward and aft ends. The aft end of the stud includes a self-locking nut to thereby lock the stud/nut assembly against rotation relative to the rotor.