Abstract: A method for repairing a turbine nozzle segment having at least two vanes disposed between outer and inner bands includes separating the outer and inner bands from the vanes, and forming one slot for each vane through the outer band and one slot for each vane through the inner band. A newly manufactured replacement vane is provided for each one of the original vanes. Each replacement vane has an outer boss formed on an outer end thereof and an inner boss formed on an inner end thereof. Then, each outer boss is inserted into a corresponding one of the outer band slots, and each inner boss is inserted into a corresponding one of the inner band slots. Once the parts are so assembled, each outer boss is welded to the outer band on the cold side, and each inner boss is welded to the inner band on the cold side. Each replacement vane is also brazed to the outer and inner bands on the respective hot sides thereof.

Abstract: A vane adjustment mechanism, for controlling the quantity of exhaust gas including a base unit having an inner base unit and an outer base unit. The inner base unit (2A) has first and second flanges, and is forced into the outer base unit (2B). A plurality of U-shaped indentations (2c) are spaced at regular angular intervals and each indentation extends from the first flange (2a) to the second flange (2b), so that the U-shaped indentations form vane shaft holes for accommodating the vane lever units (3) when the inner base unit is inserted into the outer base unit to block the U-shaped indentations in such a way that the vane lever units are free to rotate. A link plate (4) has U-shaped indentations, in which protrusions of the vane lever units (3) engage, all along the circumferential edge of the link plate.

Abstract: A method of replacing an inlet guide vane from a lower inlet casing of a compressor, the lower inlet casing adapted to be secured to an upper inlet casing at a horizontal joint, and after removal of the upper half of the inlet casing but with a rotor of the compressor remaining in place, wherein the inlet guide vane is supported between radially inner and outer walls of the lower inlet casing, and further wherein the inlet guide vane is formed with an integral stem that extends radially through the outer wall and supports a drive gear on its outer end that engages an annular gear rack, the method including a) removing the gear on the radially outer end of the integral stem of the inlet guide vane; b) shearing the inlet guide vane into two cut portions; c) removing the cut portions from inside the lower inlet casing; and d) replacing the inlet guide vane by a modified inlet guide vane having a two-piece stem assembly that enables installation without removal of the rotor.

Abstract: An annular turbine frame has ring disposed coaxially about an axial centerline axis and includes a plurality of circumferentially spaced apart ports. A plurality of circumferentially spaced apart struts are joined radially to the ring by devises on the ring. Each strut has radially opposite first and second ends, and a through channel extending therebetween. Each of the channels is aligned with a corresponding one of the ports. Each of the ports has a port counterbore though a radially outer portion of the port forming a shoulder in the port. A seal is disposed within the port counterbore between the shoulder and the strut.

Abstract: A worked nozzle ring for a gas turbine, in particular an aircraft engine, having at least one shroud and at least one blade sheet arranged thereon, whereby, in order to create a worked nozzle ring that is easy to manufacture, the blade sheet comprises, at the frontal side, at least one two-dimensionally profiled connecting space region that is placed in a profiled opening formed in the shroud by beam cutting and is connected therewith.

Abstract: A method for repairing a turbine nozzle segment having at least one vane disposed between outer and inner bands includes separating the inner band from the nozzle segment, and joining the inner band to a newly manufactured replacement casting having an outer band and at least one vane. The replacement casting includes a mounting platform formed on one end of the vane and a boss formed on the mounting platform. A collar is joined to the inner band and has a slot formed therein. The boss is then inserted into the slot, and the mounting platform is received in a recess formed in the inner band. Joining is completed by joining the boss to the collar and the mounting platform to the inner band.

Abstract: The present invention relates to a guide vane stage of a compressor comprising an outer ring and an inner ring, which are both concentric and preferably circular. The rings are connected to each other via a series of fixed vanes, and are characterized in that at least the inner ring is provided with holes or apertures which allows one of the ends of the vanes to pass through these holes or apertures. The vanes also have at their end a second aperture intended to allow the passage of a retaining and rigidifying component having an elastic function, in order to hold them in pairs.

Abstract: An assembly comprising a ceramic vane with a metal housing cast around the ends of the vane. The ceramic vane has dovetailed shaped grooves along its edges that extend from the vane's leading edge to its trailing edge. The housing is comprised of two spaced apart walls each having dovetailed protrusions for mating with the dovetail grooves in the vanes's edges. Upon the casting of the walls to the vane at least one surface of each dovetail groove comes in contact with at least one surface of the dovetail protrusion. A crushable coating is disposed between the vane's edges and the dovetail protrusions.

Abstract: A stator assembly for a rotary machine having a shroud for a stator vane is disclosed. Various construction details are developed which limit movement of the stator vane into the flowpath by reason of the stator vane being restrained by the shroud. In one particular embodiment, a clip member extends through an opening in the tip of the vane and is disposed at a location adjacent a nonflowpath surface of the shroud to restrain the tip of the vane against inward movement through the shroud.

Abstract: The present invention relates to an improved system for installing a vane in a gas turbine. The system includes a receptor pocket positioned within a first support structure and a boot attached to a first or inner end of a vane for insertion into the receptor pocket. In a first embodiment of the present invention, the receptor pocket is formed by machining it into the support structure. In a second embodiment of the present invention, the receptor pocket is formed by an insert which is installed into the support structure. In accordance with the present invention, the inner end of the vane having the boot is first inserted into the receptor pocket. After insertion has been completed, the vane is rotated until an outer base is brought into position against an outer support structure. The outer end of the vane is then secured to the outer support structure using studs and nuts.

Abstract: A device for positioning of nozzles of a stator stage and for cooling of rotor discs in gas turbines, of the type including nozzle segments consisting of several airfoils. Each nozzle segment is connected at its top to an outer ring to define a chamber containing cooling air and is positioned at its base on an inner ring. The nozzle segments form a circumferential array about the axis of the gas turbine. In each airfoil of the nozzle segment, there is provided at least one tube, which is inserted in a corresponding duct inside the airfoil for delivering cooling air to the first and second stage discs.

Abstract: In a guide vane element for a gas turbine with a vane blade extending between a platform that is located radially inward in relation to the main housing of the gas turbine and a radially outward platform, a flange is provided on at least one edge of the platforms adjoining an adjacent second guide vane element in the circumferential direction and on the side of the platform facing away from the vane blade. The second guide vane element can be attached, via a second flange provided on a second platform on the second guide vane element. The connection of the platforms forms a cover band, or a connection between the guide vane elements that is tight, flush, and stress-free at different temperatures.

Abstract: A fan outlet guide vane includes integral outer and inner platforms conforming to arcuate sides thereof, and multiple mounting bosses on the platforms. The platform sides are arcuate to conform with the vane sides for improving aerodynamic efficiency. The multiple mounting bosses improve mounting of the vanes to corresponding supporting rings.

Abstract: Turbine nozzles and turbine moving blades of an axial-flow turbine are provided which are capable of reducing a secondary flow loss with a simple structure. A nozzle blade passage formed by nozzle blades, an outer diaphragm ring and an inner diaphragm ring is structured in such a manner that the shapes of inner and outer walls of the nozzle blades are made to be irregular so that stepped portions (h1 at the root and h2 at the tip) each having curvature R are formed. The nozzle blades are formed in such a manner that ends (Zr, Zp and Zt) of an trailing edge of the nozzle blades are positioned at the most downstream position at the central portion of the nozzle blades. Moreover, relationships Zt<Zr<Zp are satisfied. Similarly to the nozzle blade passage, the moving blades are formed in such a manner that stepped portions h3 and h4 each having curvature R are formed in the moving blade passage.

Abstract: Turbine vane segments having outer and inner bands and a vane extending therebetween are welded one to the other by E-beam welding along their adjoining margins and from the outside of the bands. The adjoining margins on the hot gas path sides of the outer and inner bands are chamfered, TIG-welded and machined to provide a smooth, continuous gas path surface. The aft hook of each segment is cut back to provide inset faces in a radially projecting flange and a flange extending axially from the radial flange. A filler piece having a body shaped to correspond to the shape of the space between the inset faces of the radial flange is E-beam welded to the radial flange. Gaps between a tongue on the filler piece and the inset faces of the axially extending flange are provided with weld filler material and TIG-welded to complete the welding of the aft hook.

Abstract: A support and locking device for nozzles of a high-pressure stage in gas turbines comprises a plurality of groups of stator vanes, which are associated with a plurality of outer sealing plates, for connection of the groups to the outer liner of the combustion chamber, and are associated with a plurality of inner sealing plates, for connection of the groups to the inner liner of the combustion chamber. Each of the groups of stator vanes is locked by an inner ring, and the ring has a first series of outer holes to reinforce this locking, and a second series, of inner, through holes, which are provided in an inner extension of the ring and are used to secure the ring itself to the structure of the gas turbine.

Abstract: A network switch for network communications includes at least one data port interface supporting a plurality of data ports transmitting and receiving data. A CPU interface is configured to communicate with a CPU, and an internal memory communicates with the at least one data port interface. A memory management unit is provided for communicating data from at least one data port interface and the memory. A communication channel is provided, for communicating data and messaging information between the at least one data port interface, the memory, and the memory management unit. The configuration of the network switch also includes a fast filtering process, with the fast filtering processor filtering packets coming into the at least one data port interface. Selective filter action is taken based upon a filtering result.

Abstract: The object of the invention is to provide an axial-flow turbine having an improved efficiency. In addition, the assembly and dismantling possibilities are to be extended. According to the invention, this is achieved in that the parting seam (17) between the outer ring (12) of the nozzle ring (15) and the cover (8) is arranged on the moving-blade side of an imaginary plane (20) passing through the center of the gap width (19) of the axial gap (18).

Abstract: A turbomachine stator vane set includes a ring of vanes having platforms arranged in a housing formed on an outer shell. The bottom of the housing has a non-planar surface which is spherical or cylindrical with a radius of curvature R, and the cooperating surface of the platforms has a corresponding non-planar surface which is spherical or cylindrical with a larger radius of curvature R+&Dgr;R prior to fitting and which is reduced to the radius R under stress, by the action of fastening rivets used to assemble the vane platforms with the outer shell.

Abstract: A turbine guide blade includes a platform which absorbs thermal loads and a fastening region adjoining the platform for absorbing mechanical loads. The fastening region has such a slim construction that it leaves a cold side of the platform readily accessible.

Abstract: A method of increasing low cycle fatigue life of a turbine nozzle comprising a plurality of stationary airfoils extending between radially inner and outer ring segments comprising a) providing at least one radial passage in each of the plurality of airfoils; b) installing a rod in the radial passage extending between the radially inner and outer ring segments and fixing one end of the rod to one of the inner and outer rings; and c) pre-loading the rod to compress the airfoil between the inner and outer ring segments.

Abstract: The present invention provides a stationary blade of integrated segment construction, in which a thermal barrier coating can be applied to the whole blade surface and excessive stress can be avoided in a shroud. A plate seat connector is provided at each end face portion of an inside shroud and an outside shroud attached to outside and inside ends of gas turbine stationary blade. Several stationary blades are integrated by joining the plate seat connectors of the adjacent shrouds by means of bolts and nuts to provide a stationary blade of integrated segment construction.

Abstract: The gas turbine stator vane structure comprising a plurality of vanes 13, an outer platform 11 and an inner platform 12 is formed by integrally connecting a plurality of units 2 in a circle with fiber-reinforced prepreg tapes 10, 10′ each wound around and fused to an outside surface of the outer platform 11 and an inside surface of the inner platform 12. Each of the units 2 is constituted by (a) a core 3 composed of a laminate of fiber-reinforced prepregs and integrally having a web 31 for constituting a vane 13, and flanges 32, 33 integrally connected to both ends of the web 31 for constituting outer and inner platform pieces 21, 22; and (b) a skin layer 4 integrally molded around the core 3. The core 3 is at least partially exposed through windows of the skin layer 4 on both of an outside surface of the outer platform piece 21 and an inside surface of the inner platform piece 22, and fused to the fiber-reinforced prepreg tapes 10, 10′.

Abstract: The invention is a turbomachinery module (10) whose forwardmost vanes, which are the most damage susceptible vanes in the module, are easily removable and replaceable without substantial disassembly of the module. The module includes a case (12) and a forwardmost array (1V) of vanes. Each vane (34) of the forwardmost array has an axially proximal and distal end (90, 92) relative to the forward end (16) of the case. The distal end of each vane has a foot (102) that abuts but is not connected to a vane guide (32) on the case. The proximal end of each vane has an attachment bracket (110) that can be secured to or disengaged from a vane support (28) on the case. Vane removal is accomplished by disengaging the attachment bracket (110) from the vane support (28) and withdrawing the vane through the forward end of the case. The invention improves upon conventional turbine modules in which the forwardmost vane array is removable only from the aft end of the case after the module has been substantially disassembled.