Abstract: Disclosed is a process of fabricating a fuel nozzle assembly. The process includes providing a fuel nozzle end cover, positioning a fuel nozzle ring having a stepped geometry within a cavity of the fuel nozzle end cover, and securing the fuel nozzle ring to the fuel nozzle end cover by welding or brazing to form features corresponding to one or more of the fuel nozzle end cover and a fuel nozzle insert. The process further includes securing the fuel nozzle insert to the fuel nozzle cover by direct contact with the fuel nozzle ring.

Abstract: A venturi assembly for a turbine combustor includes a first outer annular wall and a second intermediate annular wall radially spaced from each other in substantially concentric relationship. The first outer annular wall and said second intermediate annular wall shaped to define a forward, substantially V-shaped throat region, and an aft, axially extending portion. A third radially innermost annular wall is connected to the second intermediate annular wall at an aft end of said throat region. A first plurality of apertures is provided in the first outer annular wall in the substantially V-shaped throat region, and a second plurality of apertures is provided in the aft, axially extending portion of said second intermediate annular wall so that cooling air flows through the first and second pluralities of apertures to impingement cool the third radially innermost annular wall.

Abstract: A system for detecting defects in a turbine rotor blade of a combustion turbine engine. The system may include: a turbine rotor blade that includes an insulator coating; a first electrode that is electrically connected to the turbine rotor blade; a second electrode that resides in proximity to the turbine rotor blade; means for inducing a voltage across the first electrode and the second electrode; and means for detecting current flowing between the first electrode and the second electrode.

Abstract: Disclosed is a process of fabricating a fuel nozzle assembly, a process of fabricating a fuel nozzle ring, and a fuel nozzle ring. The process of fabricating the fuel nozzle assembly includes providing a fuel nozzle end cover, positioning a fuel nozzle ring within a cavity of the fuel nozzle end cover, and securing the fuel nozzle ring to the fuel nozzle end cover to form features corresponding to one or more of the fuel nozzle end cover and a fuel nozzle insert. The process of fabricating the fuel nozzle ring includes forming the fuel nozzle ring with at least one surface corresponding to one or more of a fuel nozzle end cover and a fuel nozzle insert. The fuel nozzle ring includes at least one surface corresponding to one or more of a fuel nozzle end cover and a fuel nozzle insert.

Abstract: A fuel nozzle for a turbine combustor includes a nozzle head configured to supply a fuel/air mixture to a burner tube attached to said nozzle head and extending downstream of the nozzle head. The burner tube is provided with plural holes for introducing a fluid into the burner tube to thereby treat (e.g., cool) an interior wall of the burner tube by effusion.

Abstract: A venturi assembly for a turbine combustor includes a first outer annular wall and a second intermediate annular wall radially spaced from each other in substantially concentric relationship. The first outer annular wall and said second intermediate annular wall shaped to define a forward, substantially V-shaped throat region, and an aft, axially extending portion. A third radially innermost annular wall is connected to the second intermediate annular wall at an aft end of said throat region. A first plurality of apertures is provided in the first outer annular wall in the substantially V-shaped throat region, and a second plurality of apertures is provided in the aft, axially extending portion of said second intermediate annular wall so that cooling air flows through the first and second pluralities of apertures to impingement cool the third radially innermost annular wall.

Abstract: A system for detecting defects in a turbine rotor blade of a combustion turbine engine. The system may include: a turbine rotor blade that includes an insulator coating; a first electrode that is electrically connected to the turbine rotor blade; a second electrode that resides in proximity to the turbine rotor blade; means for inducing a voltage across the first electrode and the second electrode; and means for detecting current flowing between the first electrode and the second electrode.