Abstract: A liquid injection apparatus for use with a compressor having a rotor shaft and a casing part is provided. The liquid injection apparatus includes at least one conduit and at least one nozzle coupled to the conduit(s). The liquid injection apparatus is panel-shaped and has a first panel segment, a second panel segment, and at least one of: a passage defined between the first panel segment and the second panel segment, the passage sized to receive at least one of the rotor shaft and the casing part; and a third panel segment positioned between the first panel segment and the second panel segment. The third panel segment is at least in part detachable from the first panel segment and/or the second panel segment for receiving at least one of the rotor shaft and the casing part between the first panel segment and the second panel segment.

Abstract: A liquid injection apparatus for use with a compressor having a rotor shaft and a casing part is provided. The liquid injection apparatus includes at least one conduit and at least one nozzle coupled to the conduit(s). The liquid injection apparatus is panel-shaped and has a first panel segment, a second panel segment, and at least one of: a passage defined between the first panel segment and the second panel segment, the passage sized to receive at least one of the rotor shaft and the casing part; and a third panel segment positioned between the first panel segment and the second panel segment. The third panel segment is at least in part detachable from the first panel segment and/or the second panel segment for receiving at least one of the rotor shaft and the casing part between the first panel segment and the second panel segment.

Abstract: A liquid injection apparatus for use with a compressor having a rotor shaft and a casing part is provided. The liquid injection apparatus includes at least one conduit and at least one nozzle coupled to the conduit(s). The liquid injection apparatus is panel-shaped and has a first panel segment, a second panel segment, and at least one of: a passage defined between the first panel segment and the second panel segment, the passage sized to receive at least one of the rotor shaft and the casing part; and a third panel segment positioned between the first panel segment and the second panel segment. The third panel segment is at least in part detachable from the first panel segment and/or the second panel segment for receiving at least one of the rotor shaft and the casing part between the first panel segment and the second panel segment.

Abstract: A method of constructing a gas turbine system may include placing a foundation interface of a gas turbine mannequin on a foundation, aligning the gas turbine mannequin with a load and connecting the gas turbine mannequin to the load. The method may include constructing a pipeline and connecting the pipeline to the gas turbine mannequin. The method may include placing a foundation interface of a gas turbine mannequin on a foundation, aligning the gas turbine mannequin with an exhaust structure and connecting the gas turbine mannequin to the exhaust structure. The method also includes removing the gas turbine mannequin and installing a gas turbine.

Abstract: A progressive shipping stand includes a stage one assembly, and a stage two assembly. The stage one assembly and the stage two assembly together define a first profile, and the stage two assembly alone defines a second profile, smaller than the first profile. The stage two assembly may be attachable directly to a load. The stage two assembly is operable independently in a discrete support configuration and is selectively cooperable with the stage one assembly in a full support configuration. The shipping support allows for large machinery such as a turbine or the like to meet at least one shipping criteria that would not otherwise be feasible using a standard shipping support.

Abstract: A method of constructing a gas turbine system may include placing a foundation interface of a gas turbine mannequin on a foundation, aligning the gas turbine mannequin with a load and connecting the gas turbine mannequin to the load. The method may include constructing a pipeline and connecting the pipeline to the gas turbine mannequin. The method may include placing a foundation interface of a gas turbine mannequin on a foundation, aligning the gas turbine mannequin with an exhaust structure and connecting the gas turbine mannequin to the exhaust structure. The method also includes removing the gas turbine mannequin and installing a gas turbine.

Abstract: A support assembly for supporting a gas turbine during a manufacturing configuration, a shipping configuration and an operating configuration. The support assembly includes a stand leg securable to a base, and the stand leg includes a turbine casing interface with a slot sized to receive a turbine casing pin. A support plate is attachable to the turbine casing interface. The support plate includes a closed pin aperture that is sized to fit over the turbine casing pin in the slot. The slot is a U-shaped slot in the turbine casing interface, and the U-shaped slot is open to receive the turbine casing pin from above.

Abstract: An assembly for securing machinery such as a gas turbine on a deck includes a first block unit configured to restrict vertical displacement of the machinery relative to the deck, and a second block unit configured to restrict axial and lateral displacement of the machinery. The first block unit includes a base block securable to the deck and an attachment block secured to the base block. The second block unit is engageable with the machinery base.

Abstract: A support assembly supports a gas turbine in a manufacturing configuration, a shipping configuration and an operating configuration. The support assembly includes a stand leg securable to a base, where the stand leg includes a turbine casing interface with a slot sized to receive a turbine casing pin. A support plate attachable to the turbine casing interface includes a pin aperture that is sized to fit over the turbine casing pin in the slot.

Abstract: An assembly for securing machinery such as a gas turbine on a deck includes a first block unit configured to restrict vertical displacement of the machinery relative to the deck, and a second block unit configured to restrict axial and lateral displacement of the machinery. The first block unit includes a base block securable to the deck and an attachment block secured to the base block. The second block unit is engageable with the machinery base.

Abstract: A support assembly supports a gas turbine in a manufacturing configuration, a shipping configuration and an operating configuration. The support assembly includes a stand leg securable to a base, where the stand leg includes a turbine casing interface with a slot sized to receive a turbine casing pin. A support plate attachable to the turbine casing interface includes a pin aperture that is sized to fit over the turbine casing pin in the slot.

Abstract: A progressive shipping stand includes a stage one assembly, and a stage two assembly. The stage one assembly and the stage two assembly together define a first profile, and the stage two assembly alone defines a second profile, smaller than the first profile. The stage two assembly may be attachable directly to a load. The stage two assembly is operable independently in a discrete support configuration and is selectively cooperable with the stage one assembly in a full support configuration. The shipping support allows for large machinery such as a turbine or the like to meet at least one shipping criteria that would not otherwise be feasible using a standard shipping support.

Abstract: A liquid injection apparatus for use with a compressor having a rotor shaft and a casing part is provided. The liquid injection apparatus includes at least one conduit and at least one nozzle coupled to the conduit(s). The liquid injection apparatus is panel-shaped and has a first panel segment, a second panel segment, and at least one of: a passage defined between the first panel segment and the second panel segment, the passage sized to receive at least one of the rotor shaft and the casing part; and a third panel segment positioned between the first panel segment and the second panel segment. The third panel segment is at least in part detachable from the first panel segment and/or the second panel segment for receiving at least one of the rotor shaft and the casing part between the first panel segment and the second panel segment.

Abstract: A quick disengaging field joint connects a first component of an exhaust system of a gas turbine engine to a second component of the exhaust system. The field joint includes a pair of opposed stepped liners connected via exterior-facing connecting flanges. The field joints can be disassembled entirely from outside the exhaust housing without requiring access to the interior of the exhaust housing.

Abstract: A system adjusts positions of gas turbine inlet guide vanes (IGVs) and variable stator vanes (VSVs). The system includes a hydraulic power unit providing a supply of hydraulic fluid, an IGV servo in fluid communication with the hydraulic power unit, and a VSV servo in fluid communication with the hydraulic power unit. An IGV cylinder set is provided in fluid communication with the hydraulic power unit via the IGV servo and is connected to the IGVs. The IGV cylinder set effects displacement of the IGVs between a closed position and a fully open position. A VSV cylinder set is provided in fluid communication with the hydraulic power unit via the VSV servo. The VSVs include multiple stages linked together with a torque shaft. The VSV cylinder set is connected to the torque shaft, and the VSV cylinder set effects simultaneous displacement of the stages of the VSVs between a closed position and a fully open position.

Abstract: A quick disengaging field joint connects a first component of an exhaust system of a gas turbine engine to a second component of the exhaust system. The field joint includes a pair of opposed stepped liners connected via exterior-facing connecting flanges. The field joints can be disassembled entirely from outside the exhaust housing without requiring access to the interior of the exhaust housing.

Abstract: A system adjusts positions of gas turbine inlet guide vanes (IGVs) and variable stator vanes (VSVs). The system includes a hydraulic power unit providing a supply of hydraulic fluid, an IGV servo in fluid communication with the hydraulic power unit, and a VSV servo in fluid communication with the hydraulic power unit. An IGV cylinder set is provided in fluid communication with the hydraulic power unit via the IGV servo and is connected to the IGVs. The IGV cylinder set effects displacement of the IGVs between a closed position and a fully open position. A VSV cylinder set is provided in fluid communication with the hydraulic power unit via the VSV servo. The VSVs include multiple stages linked together with a torque shaft. The VSV cylinder set is connected to the torque shaft, and the VSV cylinder set effects simultaneous displacement of the stages of the VSVs between a closed position and a fully open position.