Labyrinth Seal Patents (Class 415/173.5)
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Patent number: 6860718Abstract: A geothermal turbine comprises a turbine casing, a turbine rotor shaft, a plurality of nozzle diaphragm outer rings fixed to the turbine casing, a plurality of nozzle diaphragm inner rings located radially inside the nozzle diaphragm outer rings, a plurality of nozzles placed between the nozzle diaphragm outer rings and the nozzle diaphragm inner rings, which form a steam passage, a plurality of rotor blades mounted on the turbine rotor shaft, which face the nozzles and form a blade cascade in a circumferential direction, a shroud arranged on tip of the rotor blade, an overhang attached to the nozzle diaphragm outer ring, which extends downstream of the nozzles and has an inner surface facing radially outside the shroud, and a plurality of sealing fins which protrude radially outward from the shroud and face the overhang.Type: GrantFiled: January 27, 2003Date of Patent: March 1, 2005Assignee: Kabushiki Kaisha ToshibaInventors: Atsuhide Suzuki, Toshihiro Fujiwara, Masataka Fukuda, Kazuaki Ikeda, Toshihiro Matsuura, Osamu Watanabe, Hisao Fujihashi, Kentaro Takagi
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Patent number: 6779970Abstract: Balancing piston for centrifugal compressors, to control and damp subsynchronous vibrations, comprising a cylindrical body which is secured onto the rotor and a cylindrical structure which contains the body on the stator side with interposition of a seal with small cells wherein the play between the rotor and the stator increased in the direction of the flow of gas through the play.Type: GrantFiled: June 11, 2002Date of Patent: August 24, 2004Assignee: Nuovo Pignone Holding S.p.A.Inventors: Massimo Camatti, Andrea Bernocchi
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Patent number: 6742783Abstract: A seal segment (66) as described for a seal segment ring (64) of a turbine (16) in a gas turbine engine (10). The seal segment (66) has an inner surface (70) adapted to face the turbine blades (36) in use. Path means (72) is defined in the seal segment (66). The path means (72) is adapted to extend, in use, generally parallel to the principal axis of the turbine and has downstream inlet means (74) through which a cooling fluid to cool the seal segment can enter the path means (72) and upstream outlet means (76) from which the cooling fluid can be exhausted from the path means (72). The cooling fluid can flow along the path means (72) in a generally upstream direction opposite to the flow of gas through the turbine.Type: GrantFiled: November 14, 2001Date of Patent: June 1, 2004Assignee: Rolls-Royce plcInventors: Steven D Lawer, Mark A Halliwell
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Publication number: 20040086377Abstract: A rotor system for a gas turbine engine is provided having an outer rotor which includes an annular outer spool that comprises at least one ring portion of increased thickness with respect to the remainder of the outer spool, attached to a relatively thinner, axially extending arm portion. A plurality of outer turbine blades are attached to the ring portion of the outer spool and extend radially inwardly into a working gas flowpath of the engine. A casing surrounds the outer spool and defines an annular cavity between the casing and the outer spool, which is sealed by forward and aft brush seals at the forward and aft ends thereof. At least one inlet port is formed through the casing for admitting a flow of cooling air to the annular cavity. Means are provided for directing this cooling air flow to the ring portion of the outer spool.Type: ApplicationFiled: October 31, 2002Publication date: May 6, 2004Applicant: General Electric CompanyInventors: Robert Proctor, James Patrick Dolan, John Christopher Brauer, Christopher Charles Glynn, Kenneth Martin Lewis
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Patent number: 6722846Abstract: Spline seals are disposed in circumferentially registering slots of adjacent arcuate seal strip segments disposed in grooves of diaphragm assemblies of a steam turbine in radial opposition to the rotating tips of the buckets. The spline seals extend in the gaps between the endfaces of the segments and minimize or preclude steam leakage past the endfaces. The spline seals are disposed in slots which may be formed as part of original equipment manufacture or may be machined in segments with the spline seals provided as retrofits.Type: GrantFiled: July 30, 2002Date of Patent: April 20, 2004Assignee: General Electric CompanyInventor: Steven Sebastian Burdgick
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Publication number: 20040022626Abstract: Spline seals are disposed in circumferentially registering slots of adjacent arcuate seal strip segments disposed in grooves of diaphragm assemblies of a steam turbine in radial opposition to the rotating tips of the buckets. The spline seals extend in the gaps between the endfaces of the segments and minimize or preclude steam leakage past the endfaces. The spline seals are disposed in slots which may be formed as part of original equipment manufacture or may be machined in segments with the spline seals provided as retrofits.Type: ApplicationFiled: July 30, 2002Publication date: February 5, 2004Inventor: Steven Sebastian Burdgick
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Patent number: 6679681Abstract: Steam turbine buckets have radially projecting tenons received in openings of covers. The covers are provided with a profiled surface, with recesses or radially outwardly projecting teeth, or both, to form a gap between the cover and a stationary component having increased pressure drop with resulting decreased leakage flow and reduced potential for solid particle erosion. In the profiled cover surface, the outer surface of the tenon and outer surface of the cover are machined to form the recesses or teeth, affording a flush cover/tenon design with improved sealing efficiencies and reduced solid particle erosion.Type: GrantFiled: April 10, 2002Date of Patent: January 20, 2004Assignee: General Electric CompanyInventors: Mark Edward Burnett, Daniel Randolph Trembley, Maurice David Fournier
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Patent number: 6652226Abstract: A gas turbine engine includes a non-rotatable member that includes a honeycomb seal that reduces wear to rotor seal teeth disposed within the gas turbine engine. The gas turbine engine also includes a rotatable annular member including a sealing assembly disposed between rotor and stator components. The rotatable annular member includes seal teeth that extend radially outward from the rotatable annular member. The stator components include a non-rotatable member that includes a honeycomb seal that extends radially inward. The honeycomb seal is fabricated from a material that has a melting temperature less than approximately 2000° F.Type: GrantFiled: February 9, 2001Date of Patent: November 25, 2003Assignee: General Electric Co.Inventors: Richard William Albrecht, Jr., Joseph Charles Kulesa, Robert Paul Czachor, Shesh Krishna Srivatsa, Daniel Edward Wines, Thomas Tracy Wallace
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Patent number: 6654437Abstract: The invention relates to a method of repairing the labyrinth seal of a diffuser in a primary pump, the diffuser being of the type comprising a peripheral skirt and a circular end wall having an orifice provided with the labyrinth seal. The method consists in making a bore in the circular end wall having a diameter greater than that of the orifice, in reducing the thickness of the remaining portion of the end wall, in forming a chamfer on the edge of the bore, in positioning a replacement part in said bore, the replacement part including a central orifice and a chamfer on its own peripheral edge, in making a bead of welding between the chamfers, and in making a new labyrinth seal in the central orifice of the replacement part.Type: GrantFiled: March 12, 2002Date of Patent: November 25, 2003Assignee: Jeumont S.A.Inventor: Louis Mazuy
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Patent number: 6644914Abstract: A sealing element (30) for a turbine of a gas turbine engine includes a radially inner surface region provided with an integrally formed seal structure (38) comprising a plurality of radially inwardly projecting walls (40). The walls may be abradable and may define cells (44) for receiving an abradable sealing material.Type: GrantFiled: March 23, 2001Date of Patent: November 11, 2003Assignee: Rolls-Royce plcInventors: Steven D Lawer, Mark A Halliwell
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Patent number: 6638012Abstract: The invention relates to an arrangement of guide vane platforms forming the inner contour of the flow channel in an axial-throughflow gas turbine and to a method for reducing the gap losses and for the improved cooling of the wall segments. In order to avoid the disadvantages of the generic solutions, particularly to achieve reduced thermal stress on the stator housing and on the connected vane platforms and subsequently to introduce the cooling air expended for this purpose into the flow channel in such a way that the gap losses of the shrouds of the moving blades are reduced, it is proposed, according to the invention, by dispensing with heat shields, to form the inner contour of the flow channel 13 at least predominantly by means of the guide vane platforms 9 and 10 and to arrange the transitional regions 16 between the platforms 9 and 10 within the cavity 12 formed by the continuous sealing ribs 3 and 4 of the shroud 2.Type: GrantFiled: December 10, 2001Date of Patent: October 28, 2003Assignee: Alstom (Switzerland) LtdInventor: Igor Bekrenev
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Publication number: 20030194312Abstract: Steam turbine buckets have radially projecting tenons received in openings of covers. The covers are provided with a profiled surface, with recesses or radially outwardly projecting teeth, or both, to form a gap between the cover and a stationary component having increased pressure drop with resulting decreased leakage flow and reduced potential for solid particle erosion. In the profiled cover surface, the outer surface of the tenon and outer surface of the cover are machined to form the recesses or teeth, affording a flush cover/tenon design with improved sealing efficiencies and reduced solid particle erosion.Type: ApplicationFiled: April 10, 2002Publication date: October 16, 2003Inventors: Mark Edward Burnett, Daniel Randolph Trembley, Maurice David Fournier
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Patent number: 6632069Abstract: Imperfect design of shroud or identical parts of the blades of steam/gas turbines, including the adjoining seals, leads to the decrease in reliability and efficiency. These drawbacks are eliminated by way of drilling of radial holes in the shroud of the blades. The transfer of steam through the shroud holes results in the relief of the pressures gradient on the surface of the shroud and prevents the formation of metal oxide, salt and other deposits on the inner surfaces of the shroud. The quantity and diameter of the holes, as well as their corresponding disposition and the values of radial clearances in shroud crowning seals regulate their efficiency.Type: GrantFiled: October 2, 2001Date of Patent: October 14, 2003Inventors: Oleg Naljotov, Vladlen Zitin
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Patent number: 6622490Abstract: An axially loaded floating brush seal useful in a stationary gas turbine engine having a first rotary compressor component having a rotor having a radial surface, a second non-rotary component having an end ending near the radial surface with the floating brush seal being positioned between the first and the second components to substantially reduce the flow of air between the first and second components. A method for controlling the flow of cooling air into a chamber in the second component using the rotary brush seal is also disclosed.Type: GrantFiled: January 11, 2002Date of Patent: September 23, 2003Assignee: Watson Cogeneration CompanyInventor: Steve Ingistov
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Material treatment for reduced cutting energy and improved temperature capability of honeycomb seals
Patent number: 6610416Abstract: The present invention provides for a method to reduce the strength of the honeycomb of a jet turbine stator, increasing its machinability, with a resultant reduction in measured peak tooth temperature, while maintaining or even improving its high temperature capability, so as not to limit its operating environment. The air seal functionality is unaffected, and even improved in some instances. The machinability of the honeycomb is increased by using a light element diffused into the honeycomb ribbon to produce the effect of reducing its strength and ductility while maintaining the environmental resistance needed. The present invention also includes the stator honeycomb produced by the foregoing method.Type: GrantFiled: April 26, 2001Date of Patent: August 26, 2003Assignee: General Electric CompanyInventors: Thomas Tracy Wallace, Brent Ross Tholke -
Patent number: 6575693Abstract: Between the rotor and stator of an axial turbo machine, sealing strips of a labyrinth seal that are mortised into sealing strip grooves are provided. Between the sealing strips relief grooves are provided in such a way that the axial stiffness of the rotor or stator is essentially steady. This may be achieved by one or more flat relief grooves, a corrugated surface, or by filling the relief grooves entirely or partially with a suitable, elastic material so that a more even axial tension distribution is achieved between the sealing strip grooves and relief grooves along the rotor or stator section.Type: GrantFiled: June 25, 2001Date of Patent: June 10, 2003Assignee: Alstom (Switzerland) LtdInventors: Joerg Pross, Thomas Kramer, Ulrich Waltke
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Patent number: 6575698Abstract: A honeycomb structure is arranged on a stator of a gas turbine and is arranged opposite the moving blades of the gas turbine. The honeycomb structure is composed of metal sheets in such a way that webs having double the sheet thickness are obtained and connections of single thickness are obtained between the webs. The angle &agr; between the circumferential direction of the stator and the webs of double thickness is 5° to 175°. This serves to avoid undesirable efforts such as, for example, overheating during friction at the honeycomb structure of the moving blades of the gas turbine.Type: GrantFiled: July 3, 2001Date of Patent: June 10, 2003Assignee: Alstom (Switzerland) LtdInventors: Alexander Beeck, Ulrich Rathmann, Hans E. Wettstein
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Patent number: 6565314Abstract: The knife edge air seal ring of a gas turbine is modified to receive a replacement or second seal ring portion having a wire brush seal. The replacement or wire brush air seal ring is mounted with the existing knife edge air seal mounting ring at a location so that the existing mounting ring may be used, while providing adequate strength and structural support for installation of the second, wire brush seal ring. The replacement seal ring may be provided with knife edge seals as well, if desired.Type: GrantFiled: December 18, 2001Date of Patent: May 20, 2003Assignee: General Electric CompanyInventors: Keith A. Marler, Matthew C. Lau, Shawn K. Smith
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Patent number: 6491498Abstract: An improved gas turbine blade is disclosed that utilizes a blade tip shroud with tapered shroud pockets to remove excess weight from the shroud while not compromising shroud bending stresses. Excess shroud weight removed by the tapered pockets reduces overall blade pull while maintaining material necessary to increase shroud stiffness. The resulting rib created between the tapered pockets provides a surface, away from possible areas of stress concentration, for drilling radial cooling holes.Type: GrantFiled: October 4, 2001Date of Patent: December 10, 2002Assignee: Power Systems MFG, LLC.Inventors: Richard Seleski, Remo Chiurato
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Publication number: 20020164247Abstract: A turbomachine for moving air includes a shroud 12 disposed about an axis A. The shroud 12 has a pair of opposing faces 14 and 16 defining a gap 18 therebetween. The opposing faces are disposed generally transversely with respect to the axis. A rotor assembly 13 is mounted for rotation about the axis. The rotor assembly has a plurality of blades 22 with tips of the blades being coupled to an annular band 30. At least a portion 32 of the annular band is disposed in the gap 18. Seal structure 36 extends from each opposing face of the shroud and into the gap to reduce swirl and minimize air leakage across the gap.Type: ApplicationFiled: May 2, 2001Publication date: November 7, 2002Inventors: Sylvain Nadeau, William Holmes
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Patent number: 6439844Abstract: The adjoining edges of bucket covers are sealed one to the other. A brush seal projecting from a stationary shroud overlies the bucket covers. A joint at which the adjacent covers sealingly engage each other precludes radial outflow of high pressure fluid into bristles of the brush seal, preventing radial and axial deflection of the bristles and consequent failure of the bristles. The joints between the covers may comprise lap or tongue-and-groove joints.Type: GrantFiled: December 11, 2000Date of Patent: August 27, 2002Assignee: General Electric CompanyInventors: Norman Arnold Turnquist, Lawrence D. Willey, Christopher Edward Wolfe
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Patent number: 6435822Abstract: In a fluid machine such as multistage centrifugal compressor, the pressure of a working fluid is raised with the rotation of a impeller. A shaft sealing device is mounted at the end of the rotary shaft in order to prevent the working gas of the raised pressure from leaking out of the fluid machine and then polluting the surroundings. In a case where the fluid machine operates to rotate at high speed, a labyrinth sealing device is employed for the purpose of reducing a frictional loss in the shaft sealing device. The labyrinth sealing device includes a plurality of stages of labyrinth fins which are formed on a casing or the rotary shaft, and a layer of abradable coating to-be-bitten which is formed in the surface part of the rotary shaft or the casing opposing to the labyrinth fins. The clearances between the labyrinth fins and the rotary shaft or the casing are made narrower on the low-pressure side of the labyrinth sealing device than on the high-pressure side thereof.Type: GrantFiled: May 25, 2001Date of Patent: August 20, 2002Assignee: Hitachi, Ltd.Inventors: Hiromi Kobayashi, Hideo Nishida, Haruo Miura, Takashi Eino, Kazuki Takahashi
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Patent number: 6431827Abstract: A diaphragm has an annular groove formed of deep and shallow grooves with the deep groove opening into the shallow groove. A combination spill strip/brush seal is disposed in the groove. The brush seal comprises a pair of flexible bars secured to the proximal ends of the brush bristles by welding and is received in the shallow groove and a recess in an axial face of the spill strip. The spill strip has base portions extending into the deep groove. The combination spill strip/brush seal is secured in the annular groove by peening material of the diaphragm into the spill strip/brush seal combination. The brush seal may be used with different diameters of spill strips and diaphragm grooves.Type: GrantFiled: December 21, 2000Date of Patent: August 13, 2002Assignee: General Electric CompanyInventors: Christopher Edward Wolfe, Norman Arnold Turnquist, Frederick George Baily, David Robert Skinner
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Patent number: 6422815Abstract: The knife edge air seal ring of a gas turbine is modified to receive a replacement or second seal ring portion having a wire brush seal. The replacement or wire brush air seal ring is mounted with the existing knife edge air seal mounting ring at a location so that the existing mounting ring may be used, while providing adequate strength and structural support for installation of the second, wire brush seal ring. The replacement seal ring may be provided with knife edge seals as well, if desired.Type: GrantFiled: March 2, 2000Date of Patent: July 23, 2002Assignee: General Electric CompanyInventors: Keith A. Marler, Matthew C. Lau, Shawn K. Smith
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Publication number: 20020085909Abstract: The invention relates to an arrangement of guide vane platforms forming the inner contour of the flow channel in an axial-throughflow gas turbine and to a method for reducing the gap losses and for the improved cooling of the wall segments.Type: ApplicationFiled: December 10, 2001Publication date: July 4, 2002Inventor: Igor Bekrenev
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Publication number: 20020081195Abstract: A diaphragm has an annular groove formed of deep and shallow grooves with the deep groove opening into the shallow groove. A combination spill strip/brush seal is disposed in the groove. The brush seal comprises a pair of flexible bars secured to the proximal ends of the brush bristles by welding and is received in the shallow groove and a recess in an axial face of the spill strip. The spill strip has base portions extending into the deep groove. The combination spill strip/brush seal is secured in the annular groove by peening material of the diaphragm into the spill strip/brush seal combination. The brush seal may be used with different diameters of spill strips and diaphragm grooves.Type: ApplicationFiled: December 21, 2000Publication date: June 27, 2002Inventors: Christopher Edward Wolfe, Norman Arnold Turnquist, Frederick George Baily, David Robert Skinner
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Publication number: 20020071764Abstract: The adjoining edges of bucket covers are sealed one to the other. A brush seal projecting from a stationary shroud overlies the bucket covers. A joint at which the adjacent covers sealingly engage each other precludes radial outflow of high pressure fluid into bristles of the brush seal, preventing radial and axial deflection of the bristles and consequent failure of the bristles. The joints between the covers may comprise lap or tongue-and-groove joints.Type: ApplicationFiled: December 11, 2000Publication date: June 13, 2002Applicant: General Electric CompanyInventors: Norman Arnold Turnquist, Lawrence D. Willey, Christopher Edward Wolfe
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Patent number: 6375416Abstract: Apparatus for reducing acoustic radiation which occurs during the operation of turbomachinery includes a shroud having a generally cylindrical inner surface and a coaxial rotor having a plurality of blades extending generally radially outwardly at equally spaced circumferential locations. The inner surface of the shroud is circumferentially contoured such that the tip clearance between each of said blades and the inner surface is caused to vary in a periodic manner upon rotation of said rotor. This creates a new periodic unsteady pressure field which is substantially equal to, and out of phase with, an existing periodic pressure field resulting from nonuniform inflow into the blades and results in the radiation from the turbomachinery of reduced blade rate frequency tones. The inner surface of the shroud may have a circumferential sinusoidal contour whose periodicity is an integral multiple of the number of the blades.Type: GrantFiled: July 15, 1993Date of Patent: April 23, 2002Inventors: Kevin J. Farrell, Walter S. Gearhart
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Patent number: 6350102Abstract: A turbine assembly includes a plurality of rotor blades comprising a root portion, an airfoil having a pressure sidewall and a suction sidewall, and a top portion having a cap. An outer shroud is concentrically disposed about said rotor blades, said shroud in combination with said tip portions defining a clearance gap. At least one circumferential shroud leakage discourager is disposed within the shroud. The leakage discourager(s) increase the flow resistance and thus reduce the flow of hot gas flow leakage for a given pressure differential across the clearance gap to improve overall turbine efficiency.Type: GrantFiled: July 19, 2000Date of Patent: February 26, 2002Assignee: General Electric CompanyInventors: Jeremy Clyde Bailey, Ronald Scott Bunker
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Publication number: 20020015641Abstract: The invention relates to a honeycomb structure (1) which is arranged on a stator of a gas turbine and which is arranged opposite the moving blades of the gas turbine. The honeycomb structure (1) is composed of metal sheets (5) in such a way that webs (3) having double the sheet thickness are obtained and connections (4) of single thickness are obtained between the webs (3). The angle (&agr;) between the circumferential direction (2) of the stator and the webs (3) of double thickness is 5° to 175°. This serves to avoid undesirable effects such as, for example, overheating during friction at the honeycomb structure (1) of the moving blades of the gas turbine.Type: ApplicationFiled: July 3, 2001Publication date: February 7, 2002Inventors: Alexander Beeck, Ulrich Rathmann, Hans E. Wettstein
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Patent number: 6340284Abstract: In an air-cooled turbine blade which, at the blade tip, has a shroud-band element extending transversely to the longitudinal axis of the blade, a plurality of cooling bores passing through the shroud-band element for the purpose of cooling, which cooling bores are connected on the inlet side to at least one cooling-air passage running through the turbine blade to the blade tip and open on the outlet side into the exterior space surrounding the turbine blade, improved and assured cooling is achieved owing to the fact that the cooling bores run from inside to outside in the shroud-band element at least approximately parallel to the direction of movement of the blade and in each case open upstream of the outer margin of the shroud-band element into a surface recess open toward the exterior space.Type: GrantFiled: December 23, 1999Date of Patent: January 22, 2002Assignee: Alstom (Switzerland) LtdInventors: Alexander Beeck, Ibrahim El-Nashar, Beat Von Arx, Bernhard Weigand
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Publication number: 20020006330Abstract: Between the rotor and stator of an axial turbo machine, sealing strips of a labyrinth seal that are mortised into sealing strip grooves are provided. Between the sealing strips relief grooves are provided in such a way that the axial stiffness of the rotor or stator is essentially steady. This may be achieved by one or more flat relief grooves, a corrugated surface, or by filling the relief grooves entirely or partially with a suitable, elastic material so that a more even axial tension distribution is achieved between the sealing strip grooves and relief grooves along the rotor or stator section.Type: ApplicationFiled: June 25, 2001Publication date: January 17, 2002Inventors: Joerg Pross, Thomas Kramer, Ulrich Waltke
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Publication number: 20010031201Abstract: A sealing element (30) for a turbine of a gas turbine engine includes a radially inner surface region provided with an integrally formed seal structure (38) comprising a plurality of radially inwardly projecting walls (40). The walls may be abradable and may define cells (44) for receiving an abradable sealing material.Type: ApplicationFiled: March 23, 2001Publication date: October 18, 2001Inventors: Steven D. Lawer, Mark A. Halliwell
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Patent number: 6302645Abstract: In a fluid machine such as multistage centrifugal compressor, the pressure of a working fluid is raised with the rotation of a impeller. A shaft sealing device is mounted at the end of the rotary shaft in order to prevent the working gas of the raised pressure from leaking out of the fluid machine and then polluting the surroundings. In a case where the fluid machine operates to rotate at high speed, a labyrinth sealing device is employed for the purpose of reducing a frictional loss in the shaft sealing device. The labyrinth sealing device includes a plurality of stages of labyrinth fins which are formed on a casing or the rotary shaft, and a layer of abradable coating to-be-bitten which is formed in the surface part of the rotary shaft or the casing opposing to the labyrinth fins. The clearances between the labyrinth fins and the rotary shaft or the casing are made narrower on the low-pressure side of the labyrinth sealing device than on the high-pressure side thereof.Type: GrantFiled: February 16, 2000Date of Patent: October 16, 2001Assignee: Hitachi, Ltd.Inventors: Hiromi Kobayashi, Hideo Nishida, Haruo Miura, Takashi Eino, Kazuki Takahashi
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Patent number: 6251526Abstract: The cast part (1) comprises a basic body (2) of a first material and a coating of at least one second material. The second material is applied to a co-cast skeleton structure (3) on the surface (20) of the basic body, with it forming a covering (4) or a covering layer (42).Type: GrantFiled: February 2, 1999Date of Patent: June 26, 2001Assignee: Sulzer Innotec AGInventor: Fritz Staub
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Patent number: 6238179Abstract: The object of the invention is to create a centrifugal compressor with a cooling appliance which is simpler but more effective. This is achieved by the feed device (27) for the gaseous cooling medium (31) opening into the separating gap upstream of the mainly radially extending gap region (20) of the separating gap (18).Type: GrantFiled: May 24, 1999Date of Patent: May 29, 2001Assignee: Asea Brown Boveri AGInventors: Dirk Wunderwald, Joachim Bremer, Ulf Christian Müller, Mihajlo Bothien, Jürg Greber
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Patent number: 6206642Abstract: A compressor blade that has a blade root, an airfoil having a first end, and a second end opposite the first end, the second end having at least one edge, and the airfoil is made of a first material having a first modulus of elasticity. A blade platform connects the blade root to the first end of the airfoil, and a flexible seal is connected to the airfoil adjacent the second end, and the seal is made of a second material having a modulus of elasticity that is substantially less than the first modulus of elasticity.Type: GrantFiled: December 17, 1998Date of Patent: March 27, 2001Assignee: United Technologies CorporationInventors: Alfred P. Matheny, Richard A. Holmes, Wendell V. Twelves, Jr.
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Patent number: 6203273Abstract: A rotary machine (10) having rotor elements (54-66), (114) and seal lands (86, 112) is disclosed. Various construction details are developed for facilitating assembly of the machine. In one embodiment clearances are established between rotor blades (66) and the seal land (86) which enable assembly of the components and provide for acceptable clearances at a steady-state operative condition of the engine.Type: GrantFiled: December 22, 1998Date of Patent: March 20, 2001Assignee: United Technologies CorporationInventors: Harvey I. Weiner, Christopher G. Demers