Abstract: An air bypass system for a gas turbine engine includes a nozzle for a gas turbine engine. The air bypass system includes the nozzle having an inner band, an outer band, and an airfoil extending between the inner band and the outer band. The airfoil defines an internal passage. A diaphragm includes an inner wall, a first rail, and a second rail, which collectively define a diaphragm cavity. The first rail defines a first rail aperture. A manifold is positioned in the diaphragm cavity. The manifold and the diaphragm collectively define a manifold chamber in fluid communication with the first rail aperture. A tube extends through the internal passage defined by the airfoil and into the diaphragm cavity. The tube is in fluid communication with the manifold chamber. Compressed air flows through the tube into the manifold chamber and exits the chamber through the first rail aperture.

Abstract: Various embodiments of the invention include turbine blades and systems employing such blades. Various particular embodiments include a turbine blade having: an airfoil having: a suction side; a pressure side opposing the suction side; a leading edge spanning between the pressure side and the suction side; and a trailing edge opposing the leading edge and spanning between the pressure side and the suction side, wherein the trailing edge defines a radial throat distribution between the airfoil and an adjacent airfoil; and a base connected with a first end of the airfoil along the suction side, pressure side, trailing edge and the leading edge.

Abstract: Various embodiments of the invention include turbine blades and systems employing such blades. Various particular embodiments include a turbine blade having: an airfoil having: a suction side; a pressure side opposing the suction side; a leading edge spanning between the pressure side and the suction side; and a trailing edge opposing the leading edge and spanning between the pressure side and the suction side, wherein the trailing edge defines a radial throat distribution between the airfoil and an adjacent airfoil; and a base connected with a first end of the airfoil along the suction side, pressure side, trailing edge and the leading edge.

Abstract: An air bypass system for a gas turbine engine includes a nozzle for a gas turbine engine. The air bypass system includes the nozzle having an inner band, an outer band, and an airfoil extending between the inner band and the outer band. The airfoil defines an internal passage. A diaphragm includes an inner wall, a first rail, and a second rail, which collectively define a diaphragm cavity. The first rail defines a first rail aperture. A manifold is positioned in the diaphragm cavity. The manifold and the diaphragm collectively define a manifold chamber in fluid communication with the first rail aperture. A tube extends through the internal passage defined by the airfoil and into the diaphragm cavity. The tube is in fluid communication with the manifold chamber. Compressed air flows through the tube into the manifold chamber and exits the chamber through the first rail aperture.

Abstract: A turbine portion for a gas turbine includes a first stage rotor disk having a plurality of dovetail slots, and a plurality of airfoils coupled to the first stage rotor disk. Each of the plurality of airfoils includes a radial centerline and a blade dovetail mounted in a corresponding one of the plurality of dovetail slots. At least one of the plurality of dovetail slots and the blade dovetail of one of the plurality of airfoils includes a stress reducing backcut spaced between about 1.733-inches (4.402-cm) and about 2.233-inches (5.67-cm) from the radial centerline.

Abstract: A method for removing debris from a turbine component includes routing a cleaning composition comprising fluosilicic acid through an internal passage of the turbine component, without contacting an external surface of the turbine component, to remove the debris.

Abstract: The third-stage buckets have airfoil profiles substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in inches in Table I wherein Z is a perpendicular distance from a plane normal to a radius of the turbine centerline and containing the X and Y values with the Z value commencing at zero in the X, Y plane at the radially innermost aerodynamic section of the airfoil and X and Y are coordinates defining the airfoil profile at each distance Z. The X, Y and Z values may be scaled as a function of the same constant or number to provide a scaled-up or scaled-down airfoil section for the bucket.