Abstract: A nozzle blade comprising radially inner and outer walls with an airfoil portion extending therebetween; the inner and outer walls formed with alignment features on respective oppositely-facing surfaces aligned with a longitudinal center axis through the nozzle blade.

Abstract: A nozzle assembly for a turbine that may include: (1) a nozzle blade having inner and outer sidewalls and, in part, defining a flowpath upon assembly into the turbine; (2) an outer ring; (3) a flowsplitter having a horizontal extension; (4) an interface between the outer ring and the outer sidewall having at least one of (i) a male/female interface or (ii) a radial interlock; and (5) an interface between the horizontal extension and the inner sidewall having at least one of (i) the male/female interface or (ii) the radial interlock. In some embodiments, one of the interface between the outer ring and the outer sidewall and the interface between the horizontal extension and the inner sidewall comprises a weld and one of the interface between the outer ring and the outer sidewall and the interface between the horizontal extension and the inner sidewall is weld free.

Abstract: A system in a steam turbine for removing water droplets from the flowpath of a steam turbine that may include a groove for collecting water droplets, and a plurality of moisture removal holes originating within the groove. The groove may run in a circumferential manner around an outer sidewall of the steam turbine, be axially positioned upstream and in close proximity to the leading edge of a nozzle, and have a gradual slope at a leading edge and a steep wall at a trailing edge. The moisture removal holes may be a channel through the outer sidewall through which the water droplets that collect in the groove may flow.

Abstract: A nozzle assembly for a turbine that may include: (1) a nozzle-blade having inner and outer sidewalls and, in part, defining a flowpath upon assembly into the turbine; (2) an outer ring; (3) a flowsplitter having a horizontal extension; (4) an interface between the outer ring and the outer sidewall having at least one of (i) a male/female interface or (ii) a radial interlock; and (5) an interface between the horizontal extension and the inner sidewall having at least one of (i) the male/female interface or (ii) the radial interlock. In some embodiments, one of the interface between the outer ring and the outer sidewall and the interface between the horizontal extension and the inner sidewall comprises a weld and one of the interface between the outer ring and the outer sidewall and the interface between the horizontal extension and the inner sidewall is weld free.

Abstract: A method facilitates reducing stress in a turbine bucket including a metallic base metal. The method comprises providing a turbine bucket including at least one pocket formed therein, and filling at least one pocket defined in the bucket with a polymer composite having continuous fibers oriented in a resin matrix, such that the fibers have an orientation determined in accordance with a pre-selected frequency tuning of the bucket.

Abstract: A method for making a turbine blade includes providing a bucket in the turbine blade with a plurality of window pockets passing all the way through a wall of the bucket, positioning the window pockets in regions minimizing or at least reducing stress concentrations on the window pockets, and casting a composite comprising a resin matrix and layers of a fabric material in the bucket.

Abstract: A system in a steam turbine for removing water droplets from the flowpath of a steam turbine that may include a groove for collecting water droplets, and a plurality of moisture removal holes originating within the groove. The groove may run in a circumferential manner around an outer sidewall of the steam turbine, be axially positioned upstream and in close proximity to the leading edge of a nozzle, and have a gradual slope at a leading edge and a steep wall at a trailing edge. The moisture removal holes may be a channel through the outer sidewall through which the water droplets that collect in the groove may flow.

Abstract: A cooling insert/nozzle assembly for use in gas turbines or similar machinery includes a nozzle having inner and outer ribs with cast-in “T” sections and “L” sections, respectively, at the end of the ribs in which air flow enters the nozzle. The assembly further includes a cooling insert having a flexible end which is inserted between adjacent ribs having either the cast-in “T” or “L” sections.

Abstract: The invention comprises a metering plate which is assembled to an impingement insert for use in the nozzle of a gas turbine. The metering plate can have one or more metering holes and is used to balance the cooling flow within the nozzle. A metering plate with multiple holes reduces static pressure variations which result from the cooling airflow through the metering plate. The metering plate can be assembled to the insert before or after the insert is inserted into the nozzle.

Abstract: The invention comprises a metering plate which is assembled to an impingement insert for use in the nozzle of a gas turbine. The metering plate can have one or more metering holes and is used to balance the cooling flow within the nozzle. A metering plate with multiple holes reduces static pressure variations which result from the cooling airflow through the metering plate. The metering plate can be assembled to the insert before or after the insert is inserted into the nozzle.

Abstract: A method of determining the throat area between adjacent airfoils in a nozzle set among a plurality of nozzle sets of a machine involves providing a plurality of inspection points on a suction side of a first airfoil and a pressure side of a second airfoil, the second airfoil being adjacent to the first airfoil. A plurality of inspection points are provided on each of an outer sidewall and an inner sidewall, respectively, of the nozzle set. Positions of each of the first and the second airfoils, and the outer and inner sidewalls are determined by measuring the positions of the inspection points. The measured positions of each of the first and second airfoils, and the outer sidewall and the inner sidewall are compared with corresponding predetermined values.

Abstract: A method of determining the throat area between adjacent airfoils in a nozzle set among a plurality of nozzle sets of a machine involves providing a plurality of inspection points on a suction side of a first airfoil and a pressure side of a second airfoil, the second airfoil being adjacent to the first airfoil. A plurality of inspection points are provided on each of an outer sidewall and an inner sidewall, respectively, of the nozzle set. Positions of each the first and the second airfoils, and the outer and inner sidewalls are determined by measuring the positions of the inspection points, and the measured positions of each of the first and second airfoils, and the outer sidewall and the inner sidewall are compared with corresponding predetermined values.

Abstract: A gas turbine nozzle segment has outer and inner bands and vanes therebetween. Each band includes a side wall, a cover and an impingement plate between the cover and nozzle wall defining two cavities on opposite sides of the impingement plate. Cooling steam is supplied to one cavity for flow through apertures of the impingement plate to cool the nozzle wall. The side wall of the band and inturned flange define with the nozzle wall an undercut region. Slots are formed through the inturned flange along the nozzle side wall. A plate having through-apertures extending between opposite edges thereof is disposed in each slot, the slots and plates being angled such that the cooling medium exiting the apertures in the second cavity lie close to the side wall for focusing and targeting cooling medium onto the side wall.

Abstract: A gas turbine nozzle segment has outer and inner bands and a vane therebetween. Each band includes a nozzle wall, a side wall, a cover and an impingement plate between the cover and the nozzle wall defining two cavities on opposite sides of the impingement plate. Cooling steam is supplied to one cavity for flow through apertures of the impingement plate to cool the nozzle wall. The side wall of the band and inturned flange define with the nozzle wall an undercut region. The impingement plate has a turned flange welded to the inturned flange. A backing plate overlies the turned flange and aligned apertures are formed through the backing plate and turned flange to direct and focus cooling flow onto the side wall of the nozzle segment.

Abstract: A turbine casing is provided in two casing halves joined one to the other along a horizontal splitline having flanges with spaced boltholes. A circumferentially extending rib is provided about each casing half at a location just forward of the turbine buckets to minimize or eliminate distortion caused by internal pressure and meridional roll of the casing. One or more axially extending ribs is provided on each casing half. The axial ribs have a radial stiffness which substantially matches the stiffness and thermal response of the flanges.