Abstract: A rotor and stator assembly having a rotor and a stator with opposing surfaces defining an air bearing and an air dam of an aspirating face seal. In a first embodiment, the air bearing and the air dam are axially offset. In a second embodiment, the rotor has an axially extending protuberance located radially between the air bearing and the air dam. The axial offset and the protuberance each act to divert the air flow (e.g., compressed gas or combustion gases in a gas turbine or steam in a steam turbine) in a direction transverse to the air flow direction through the air bearing and the air dam, thus isolating the air flows from the air bearing and the air dam which improves seal performance.

Abstract: The turbine nozzle diaphragm includes nozzle diaphragm segments formed of a subassembly including inner and outer spacer bands with airfoil-shaped partitions circumferentially spaced one from the other secured to the inner and outer spacer bands. Inner web and outer ring segments are secured to the inner and outer spacer band segments, respectively, to form nozzle diaphragm segment halves. End surfaces of the inner webs and outer rings lie in a plane passing through the axis of the nozzle diaphragm. The spacer bands have flanges projecting from the ends of the segments with weld material built up behind the flanges to provide additional support for the trailing edge portions of the partition adjacent the joint. Complementary recesses are formed in the opposed ends of the opposite segment whereby a Z-joint requiring limited material and labor is formed.

Abstract: The turbine includes inner and outer rings and partitions mechanically connected therebetween. In one form, the partitions have connecting elements at tip and root portions of the vanes which are received in complementary grooves in the outer and inner rings, respectively. The partitions in one form are stacked against one another and secured by end lugs at the diaphragm joints. In another form, the partitions are pinned to the outer and inner rings with spaces between the connecting elements to avoid accumulation of tolerances. In a third form, the partitions are applied against the outer and inner rings in an axial direction and retainer plates are bolted to the outer and inner rings to secure the partitions in the diaphragm assembly. In all cases, the diaphragm is formed without welding.

Abstract: A nozzle diaphragm for a turbine includes an outer ring having a groove formed along its inner surface for receiving a first locator ring, an inner web having a groove formed along its outer surface for receiving a second locator ring and partitions circumferentially spaced one from the other and connected to the outer ring and inner web. The locator rings have slots opening into the flow region for receiving tenons formed on the ends of the partitions. By precisely locating the tenons and slots, the aerodynamic characteristics of the partitions can be set during fabrication without the need for expensive and time-consuming fixtures.

Abstract: The flowpath assembly includes inner and outer circular bands 16 and 18, respectively, and a plurality of stator blades 20 extending between the bands. The tip portions 26 of the stator blades and the openings 30 in the outer bands are at least as large as the footprints F of the blades in a radial direction. Thus, the airfoil portions 22 of the blades, which are bowed, tapered and twisted, are receivable through the openings 30 in the outer band 18 during assembly. The tip and root portions 24 and 26, respectively, of the blades are secured in the openings by welding.