Labyrinth Seal Patents (Class 415/173.5)
  • Patent number: 10648484
    Abstract: A compressor for a turbine engine includes a shroud having a grooved section including a plurality of groove segments extending radially into a shroud surface. A rotor assembly rotatably supported in the shroud includes a rotor hub and a plurality of rotor blades. Each rotor blade extends radially from the rotor hub and terminates at a blade tip, which is spaced from the shroud surface by a tip gap and defines a non-constant clearance region between a leading edge position and a medial chord position along the blade chord at the minimum tip clearance. The rotor blades generate an aft axial fluid flow through the shroud and the grooved section is formed in the shroud surface upstream of the medial chord position within the non-constant clearance region for resisting a reverse axial fluid flow through the tip gap when the compressor section is operated at near stall conditions.
    Type: Grant
    Filed: February 14, 2017
    Date of Patent: May 12, 2020
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventors: Timothy Gentry, Bruce David Reynolds, Nick Nolcheff
  • Patent number: 10612407
    Abstract: A blade outer air seal (BOAS) segment according to an exemplary aspect of the present disclosure includes, among other things, a seal body having a radially inner face that circumferentially extend between a first mate face and a second mate face and axially extend between a leading edge face and a trailing edge face, wherein a radial position of the radially inner face varies at a given axial position.
    Type: Grant
    Filed: February 4, 2014
    Date of Patent: April 7, 2020
    Assignee: United Technologies Corporation
    Inventors: Paul M. Lutjen, Michael J. Bruskotter
  • Patent number: 10415591
    Abstract: A compressor may include an airfoil configured to rotate about an axis. The airfoil may have a span measured radially from a root of the airfoil to a tip of the airfoil. A compressor case may be radially adjacent to the airfoil. The airfoil and the compressor case may define a clearance between the tip of the airfoil and a radially inner surface of the compressor case. A ratio of the clearance to the span may be between 1.5 to 2.5 percent.
    Type: Grant
    Filed: September 21, 2016
    Date of Patent: September 17, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Robert W Fessenden, Abhir A Adhate, Yuan Dong, Sean Nolan, Li Xing Pan
  • Patent number: 10393132
    Abstract: A compressor (10) configured for use in a gas turbine engine (12) and having a rotor assembly (14) with a pumping system (16) positioned on a rotor drum (18) to counteract reverse leakage flow at a gap (20) formed between one or more stator vane tips (22) and a radially outer surface (24) of the rotor drum (18). The pumping system (16) may be from pumping components (26) positioned radially inward of one or more stator vane tips (22) to reduce, if not completely eliminate, reverse leakage flow at the stator vane tips (22). In at least one embodiment, the pumping component (26) may be formed from one or more cutouts (28) in the outer surface (24) of the rotor drum (18). In another embodiment, the pumping component (26) may be formed from at least one pumping fin (30) extending from the radially outer surface (24) of the rotor drum (18). In at least one embodiment, rows (32) of pumping components (26) may be aligned with rows (34) of stator vanes (36) within the compressor (10).
    Type: Grant
    Filed: August 8, 2014
    Date of Patent: August 27, 2019
    Assignee: SIEMENS AKTIENGESELLSCHAFT
    Inventors: Ching-Pang Lee, Kok-Mun Tham
  • Patent number: 10072670
    Abstract: Provided is a fan shroud assembly and, more specifically, a fan shroud assembly including a swirling airflow-preventing saw-teeth which is arranged along a predetermined inner circumferential surface of a ventilating part while maintaining a predetermined gap from an end portion of a blade of a fan or an end portion of a fan band of the fan and are formed in a saw-toothed shape, in which both a first area in which the swirling airflow-preventing saw-teeth are formed and a second area from which the swirling airflow-preventing saw-teeth are removed are formed, thereby generating a swirling airflow of ventilated air due to a reduction in pressure fluctuation and thus effectively reducing noise.
    Type: Grant
    Filed: June 19, 2014
    Date of Patent: September 11, 2018
    Assignee: HANON SYSTEMS
    Inventors: Woo Youl Jung, Cha You Lim, Yong Sung Kwon, Kyung Seok Cho
  • Patent number: 9988907
    Abstract: A turbocharger including a wheel having suction surfaces and hub surfaces contoured to reduce secondary flow. The suction surfaces are radially contoured with a sinusoidal component, and further have a chamfered edge at the shroud edge. The hub end-walls are contoured both streamwise and cross-stream with sinusoidal components.
    Type: Grant
    Filed: April 25, 2011
    Date of Patent: June 5, 2018
    Assignee: Honeywell International, Inc.
    Inventor: Cheng Xu
  • Patent number: 9863251
    Abstract: A turbomachine stage includes guide vanes and an airfoil platform forming a guide vane cascade, and rotor blades and an airfoil platform forming a rotor blade cascade. Airfoil platforms have cascade regions extending between circumferentially adjacent airfoils, and gap regions which radially and/or axially bound an axial gap extending axially between the guide vane cascade and the rotor blade cascade. A contour of at least one of these gap regions varies in the radial and/or axial direction around the circumference.
    Type: Grant
    Filed: November 28, 2012
    Date of Patent: January 9, 2018
    Assignee: MTU Aero Engines GmbH
    Inventors: Inga Mahle, Jochen Gier, Kai Koerber, Karl Engel
  • Patent number: 9765639
    Abstract: A turbine stage for a gas turbine engine is disclosed. The turbine stage includes a turbine disk and a turbine diaphragm, forming a cavity there between. The turbine stage also includes an exit flow discourager comprised of at least two teeth. The teeth may be located radially apart from each other, each tooth including a length extending in the axial direction and a width extending in the radial direction. A channel is formed between the teeth and an axially adjacent surface. A recirculation region may be formed in between each pair of teeth.
    Type: Grant
    Filed: January 10, 2014
    Date of Patent: September 19, 2017
    Assignee: Solar Turbines Incorporated
    Inventors: Yong Weon Kim, Kidon Lee
  • Patent number: 9726027
    Abstract: A turbine includes: a blade body having a blade provided at one of a rotor rotatably supported and a stator provided around the rotor and extending in a radial direction and a shroud extending in a circumferential direction at a tip portion in the radial direction of the blade; and an accommodating concave body provided at another one of the rotor and the stator, extending in the circumferential direction, accommodating the shroud with a gap interposed therebetween, and relatively rotating with respect to the blade body, wherein a leakage flow leaked from a main flow flowing along the blade flows into the gap; and wherein the shroud is provided with a guide curved surface formed between a peripheral surface facing the accommodating concave body and a trailing edge end portion formed closer to a main flow side in a downstream side of the leakage flow than the peripheral surface.
    Type: Grant
    Filed: September 8, 2011
    Date of Patent: August 8, 2017
    Assignee: MITSUBISHI HITACHI POWER SYSTEMS, LTD.
    Inventors: Yoshihiro Kuwamura, Kazuyuki Matsumoto, Hiroharu Oyama, Yoshinori Tanaka, Masaaki Matsuura, Asaharu Matsuo
  • Patent number: 9644639
    Abstract: The centrifugal compressor described includes an impeller shroud which encloses the impeller and has a curved shroud surface that extends between an inducer portion and an exducer portion. The compressor includes one or more circumferential grooves in the shroud body within the exducer portion. Each groove has opposed wall segments spaced apart therefrom. The wall segments are inclined at a nonzero groove angle relative to a normal of the shroud surface in a direction opposite the fluid flow path along the shroud surface.
    Type: Grant
    Filed: January 27, 2014
    Date of Patent: May 9, 2017
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Hien Duong, Vijay Kandasamy
  • Patent number: 9638051
    Abstract: A turbomachine bucket may include an airfoil, a shank coupled to the airfoil, and an angel wing coupled to the shank, the angel wing having an axially extending tip sized to seal with a plurality of discouragers, each discourager having a different axial extent. Various methods for modifying an angel wing to accommodate different sized discouragers are also disclosed.
    Type: Grant
    Filed: September 4, 2013
    Date of Patent: May 2, 2017
    Assignee: General Electric Company
    Inventors: Gareth William David Lewis, Andrew Daniel Grafitti, Jonathan Matthew Lomas, Felipe Roman-Morales, Ronald Lee Souther
  • Patent number: 9429022
    Abstract: A turbine includes an annular turbine blade body disposed on a flow path, a diaphragm outer ring installed at a tip side of the annular turbine blade body via a clearance, and seal fins formed to protrude from the diaphragm outer ring and configured to form small clearances with the annular turbine blade body, wherein dead water region-filling sections are formed in cavities in which main vortexes are generated, such that a dead water region that the main vortexes cannot reach is filled.
    Type: Grant
    Filed: September 15, 2011
    Date of Patent: August 30, 2016
    Assignee: MITSUBISHI HITACHI POWER SYSTEMS, LTD.
    Inventors: Kazuyuki Matsumoto, Yoshihiro Kuwamura, Hiroharu Oyama, Yoshinori Tanaka, Yukinori Machida, Asaharu Matsuo
  • Patent number: 9404378
    Abstract: A seal configuration includes a housing and a rotatable member rotationally mounted relative to the housing. The rotatable member has at least one portion defining an outer perimetrical face that is configured to contact the housing during operational conditions that cause a radial dimension of the at least one portion to increase. The at least one portion has opposing axial surfaces with each of the opposing axial surfaces being dimensionally axially nearer to the other of the opposing axial surfaces immediately radially inwardly of the outer perimetrical face than a furthest part of the outer perimetrical face.
    Type: Grant
    Filed: October 13, 2015
    Date of Patent: August 2, 2016
    Assignee: General Electric Company
    Inventors: David Richard Johns, Eric David Roush
  • Patent number: 9404370
    Abstract: An exhaust-gas turbocharger component (10) having at least one flow-conducting component surface (11) and having a discontinuity structure (12) which is formed on the component surface (11). The discontinuity structure (12) has a multiplicity of punctiform depressions (13) which are arranged separately from one another on at least one part of the component surface (11).
    Type: Grant
    Filed: August 18, 2011
    Date of Patent: August 2, 2016
    Assignee: BorgWarner Inc.
    Inventors: Timo Scheuermann, Stefan Ebert
  • Patent number: 9388701
    Abstract: A turbine (1) of the present invention comprises that at one part of a tip part (51) of the blade (50) and an area (11a) of the structure (11) corresponding to the tip part (51) of the blade, a stepped part (52) is formed, a seal fin (15) is provided at the another part of the tip part (51) of the blade and the area (11 a) of the structure (11), a cavity (C) is formed between the tip part (51) of the blade and the area (11a) of the structure (11) and between the seal fin (15) and a partition wall (54, 15). The seal fin (15) comprises a fin main body part (16), and a space restriction part (17). Thus, the present invention provides a high performance turbine in which the leakage flow rate is reduced.
    Type: Grant
    Filed: January 31, 2011
    Date of Patent: July 12, 2016
    Assignee: MITSUBISHI HITACHI POWER SYSTEMS, LTD.
    Inventors: Yoshihiro Kuwamura, Kazuyuki Matsumoto, Hiroharu Oyama, Yoshinori Tanaka, Asaharu Matsuo
  • Patent number: 9309776
    Abstract: An assembly and method are provided for sealing a compressor in a gas turbine engine. The method comprises forming an annular groove in a compressor casing such that the groove extends circumferentially about a rotor that is housed within the casing. The compressor casing is then coupled to the rotor such that the compressor casing extends circumferentially about the rotor. A plurality of arcuate seal segments are then inserted into the annular groove without removing the rotor from the compressor casing such that the plurality of seal segments extend circumferentially about the rotor to facilitate sealing a gap that is defined between the rotor and the compressor casing.
    Type: Grant
    Filed: September 11, 2012
    Date of Patent: April 12, 2016
    Assignee: General Electric Company
    Inventors: Sanji Ekanayake, Alston Ilford Scipio, Raymond Henry Goetze, Peter Samuel King, Douglas Corbin Warwick
  • Patent number: 9249667
    Abstract: A system includes a turbomachine that includes a stator and a rotor. The rotor is configured to rotate about a rotational axis relative to the stator. In addition, the rotor includes a least one rotary blade, and the at least one rotary blade has a patterned structure of beams and cavities.
    Type: Grant
    Filed: March 15, 2012
    Date of Patent: February 2, 2016
    Assignee: General Electric Company
    Inventors: Patrick Daniel Noble, Joseph Anthony Weber, Donald Earl Floyd, II
  • Patent number: 9181814
    Abstract: A gas turbine engine stator segment has a shroud band and a plurality of blade sections. Each of the blade sections has a first section with a first thickness, second section with a second thickness and a fairing section transitioning between the first and second section. The second section thickness is less than the first section thickness.
    Type: Grant
    Filed: November 24, 2010
    Date of Patent: November 10, 2015
    Assignee: United Technology Corporation
    Inventors: Hope C. Rowley, Paul W. Baumann, Edwin M. Worth, Carl S. Richardson
  • Patent number: 9103352
    Abstract: A ventilator for use in air-conditioning and refrigeration technology has a housing of plastic material in a one-part configuration having integrally formed therein an inlet nozzle, cylinder-shaped flow guiding means, outlet guide vanes, and a diffusor. A drive motor is arranged in the housing. An impeller wheel is rotatably supported about a central axis in the housing and driven by the drive motor. A protective screen is connected to the housing. A motor support is connected by the outlet guide vanes to the housing. The impeller wheel has vanes with radially outwardly positioned vane ends, wherein the vane ends are embodied as flow elements (winglets). The flow elements are spaced at a minimal spacing relative to a sidewall of the housing. The drive motor is an external rotor motor that is embodied either as an alternating current asynchronous motor (AC) or an electronically commutated direct current motor (EC).
    Type: Grant
    Filed: August 12, 2011
    Date of Patent: August 11, 2015
    Assignee: Ziehl-Abegg AG
    Inventors: Omar Sadi, Andreas Gross, Lothar Ernemann, Frieder Lörcher
  • Patent number: 9080459
    Abstract: The present application provides a stage of a gas turbine engine. The stage may include a bucket, a shroud facing the bucket, and a forward step honeycomb seal on the shroud. The forward step honeycomb seal may include a forward step portion and one or more linear portions.
    Type: Grant
    Filed: January 3, 2012
    Date of Patent: July 14, 2015
    Assignee: General Electric Company
    Inventor: Rohit Chouhan
  • Publication number: 20150118032
    Abstract: A seal system for sealing a seal gap in a turbomachine includes: a rotor component; a stator component, the sealing gap extending between the rotor component and the stator component; first seal strips and second seal strips each projecting into the seal gap and forming at least one seal strip package; first seal strip grooves in the rotor component that receive the first seal strips; second seal strip grooves in the stator component that receive the second seal strips; and a relief groove in the rotor component arranged in front of the seal strip package, and after the seal strip package. Every relief groove is at least two times wider than, and at most six times wider than, the first and second seal strip grooves and at least two times deeper than, and at most six times deeper than, the first and second seal strip grooves.
    Type: Application
    Filed: October 22, 2014
    Publication date: April 30, 2015
    Inventors: Emil Aschenbruck, Carsten Bennewa
  • Patent number: 9016692
    Abstract: In sealing rings for a labyrinth seal that are arranged on a rotationally symmetrical component and in frictional contact with a stationary run-in layer, a part of the sealing ring (8) that contacts the run-in layer is in the form of a wear protection ring segment (15) that is built up on a truncated sealing ring (14) and which includes a metal matrix (16) with wear protection particles (13) embedded therein. The manufacture of the wear protection ring segment is carried out by laser build-up welding, wherein the proportion of wear protection particles contained in the metal powder flow supplied to the laser beam can be controlled and increased in an edge or tip region of the sealing ring.
    Type: Grant
    Filed: November 24, 2010
    Date of Patent: April 28, 2015
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventors: Thomas Haubold, Andreas Kohns
  • Publication number: 20150086343
    Abstract: A device for sealing a high pressure region in a turbomachine from a low pressure region; the turbomachine has one or more statoric parts and one or more rotoric parts; the device comprises a labyrinth seal having a first plurality of grooves and a second plurality of grooves; the first plurality of grooves is disposed in a helical pattern and the second plurality of grooves is disposed in a cylindrical pattern; the labyrinth seal is disposed between at least one of the one or more rotoric parts of the turbomachine and at least one of the one or more statoric parts of the turbomachine between the high pressure region and the low pressure region of the turbomachine; the helical pattern has a helix angle less than or equal to 10°, wherein a stabilization effect of the turbomachine is obtained and leakage due to the second plurality of grooves is negligible.
    Type: Application
    Filed: April 26, 2013
    Publication date: March 26, 2015
    Inventors: Emanuele Rizzo, Antonio Pelagotti
  • Publication number: 20150086342
    Abstract: In a centrifugal pump for delivering liquids in a motor vehicle, annular webs project into a gap seal between a housing part and a cover disc of a rotor. The webs are arranged on both components of the housing part and of the cover disc and delimit chambers which accelerate, decelerate and divert a flow. In this way, the gap seal has a high throttling action.
    Type: Application
    Filed: November 9, 2012
    Publication date: March 26, 2015
    Inventor: Peter Köppler
  • Patent number: 8984895
    Abstract: A method and apparatus are disclosed for a gas turbine spool design combining metallic and ceramic components in a way that controls clearances between critical components over a range of engine operating temperatures and pressures. In a first embodiment, a ceramic turbine rotor rotates just inside a ceramic shroud and separated by a small clearance gap. The ceramic rotor is connected to a metallic volute. In order to accommodate the differential rates of thermal expansion between the ceramic rotor and metallic volute, an active clearance control system is used to maintain the desired axial clearance between ceramic rotor and the ceramic shroud over the range of engine operating temperatures. In a second embodiment, a ceramic turbine rotor rotates just inside a ceramic shroud which is part of a single piece ceramic volute/shroud assembly.
    Type: Grant
    Filed: July 11, 2011
    Date of Patent: March 24, 2015
    Assignee: ICR Turbine Engine Corporation
    Inventors: James B. Kesseli, Matthew Stephen Baldwin
  • Patent number: 8936431
    Abstract: A shroud for a turbine and a method of assembling is provided. The turbine includes a housing, a rotatable shaft and a bucket extending outward therefrom. The shroud includes an alignment member which is coupled to the housing, wherein the alignment member includes a first end, a second end and a body extending between the first and second ends. The second end includes an arcuate portion to facilitate fluid flow downstream from the bucket. The shroud further includes a seal coupled to the body to facilitate sealing a gap defined between the bucket and the body.
    Type: Grant
    Filed: June 8, 2012
    Date of Patent: January 20, 2015
    Assignee: General Electric Company
    Inventors: Rohit Chouhan, Sumeet Soni
  • Patent number: 8932001
    Abstract: Certain embodiments of the invention may include systems, methods and apparatus for providing a labyrinth seal. In an example embodiment, a method is provided for sealing a flow path between a stationary element and a rotating element of a turbomachine. The method can include disposing at least one fixture on an inner surface of a stationary element associated with the turbomachine; disposing a packing ring linked via a spring element to the fixture wherein the packing ring comprises at least one bore; and disposing, according to a predetermined profile, a plurality of interdigitated packing ring teeth and rotor teeth intermediate to the packing ring and the rotating element; wherein the bore, packing ring teeth, and rotor teeth, cooperate to counter a moment associated with one or more axial forces.
    Type: Grant
    Filed: September 6, 2011
    Date of Patent: January 13, 2015
    Assignee: General Electric Company
    Inventors: Xiaoqing Zheng, Hrishikesh Deo, Binayak Roy
  • Publication number: 20150003973
    Abstract: An outer rim seal arrangement (10), including: an annular rim (70) centered about a longitudinal axis (30) of a rotor disc (31), extending fore and having a fore-end (72), an outward-facing surface (74), and an inward-facing surface (76); a lower angel wing (62) extending aft from a base of a turbine blade (22) and having an aft end (64) disposed radially inward of the rim inward-facing surface to define a lower angel wing seal gap (80); an upper angel wing (66) extending aft from the turbine blade base and having an aft end (68) disposed radially outward of the rim outward-facing surface to define a upper angel wing seal gap (80, 82); and guide vanes (100) disposed on the rim inward-facing surface in the lower angel wing seal gap. Pumping fins (102) may be disposed on the upper angel wing seal aft end in the upper angel wing seal gap.
    Type: Application
    Filed: June 28, 2013
    Publication date: January 1, 2015
    Inventors: Ching-Pang Lee, Kok-Mun Tham, Eric Schroeder, Jamie Meeroff, Samuel R. Miller, Jr., John J. Marra, Christian X. Campbell
  • Publication number: 20140356143
    Abstract: A structural assembly for a fluid-flow machine includes: a main flow path boundary and at least one row of relatively rotating blades with a gap existing between blade ends of the at least one row of blades and the main flow path boundary. At least one secondary flow duct has in the main flow path boundary one opening each at ends spaced apart in the flow direction, such that the secondary flow duct is connected to the main flow path via the two openings. The structural assembly has at least two components connected to one another, i.e. at least one support component and at least one connecting component, where the support component at least partially forms the main flow path boundary and where the connecting component forms or surrounds at least one part-section of the secondary flow duct.
    Type: Application
    Filed: May 29, 2014
    Publication date: December 4, 2014
    Applicant: Rolls-Royce Deutschland Ltd & Co KG
    Inventor: Volker GUEMMER
  • Patent number: 8870531
    Abstract: The invention provides a turbine machine rotor having blades of composite material, the rotor comprising an assembly disk, a plurality of composite material blades mounted on the assembly disk via their roots and each provided at its free end with a platform, and a metal shroud positioned on the blade platforms concentrically around the assembly disk and including labyrinth teeth that project radially outwards in order to abrade an abradable material carried by a casing surrounding the rotor, the casing being held stationary both axially and circumferentially relative to the blade platforms and being suitable for moving radially outwards in operation relative to the blade platforms.
    Type: Grant
    Filed: December 11, 2009
    Date of Patent: October 28, 2014
    Assignee: SNECMA
    Inventors: Stephane Pierre Guillaume Blanchard, Julien Mateo, Stephane Otin
  • Patent number: 8844936
    Abstract: According to one embodiment of the disclosure, an annular seal generally includes a hollow member having two ends and an inner surface. The hollow member has a number of depressions formed in and extending around its inner surface. Each of the depressions having a depth that is a function of its distance from one of the two ends.
    Type: Grant
    Filed: December 9, 2011
    Date of Patent: September 30, 2014
    Assignee: The Texas A&M University System
    Inventor: Dara W. Childs
  • Patent number: 8834096
    Abstract: In an axial flow gas turbine efficient cooling and a long life-time can be achieved by providing the outer blade platforms (45) with a plurality of outer teeth (46a-c) running parallel to each other in the circumferential direction and being arranged one after the other in the direction of the hot gas flow. The teeth (46a-c) are divided into first and second teeth (46a; 46b-c), the second teeth (46b-c) being located downstream of the first teeth (46a), the first teeth (46a) are opposite to a downstream projection (33) of the adjacent vanes (21) of the turbine stage (TS), and the second teeth (46b-c) are opposite to the respective stator heat shields (27).
    Type: Grant
    Filed: November 29, 2011
    Date of Patent: September 16, 2014
    Assignee: Alstom Technology Ltd.
    Inventor: Alexander Anatolievich Khanin
  • Patent number: 8834107
    Abstract: The present application provides a tip clearance control system for reducing an airflow through a turbo machine. The tip clearance control system may include a casing shroud and a tip shroud positioned within the casing shroud. The tip shroud may include a first step at a leading edge and a second step adjacent to the first step. The casing shroud and the tip shroud may define a first cavity therebetween downstream of the second step.
    Type: Grant
    Filed: September 27, 2010
    Date of Patent: September 16, 2014
    Assignee: General Electric Company
    Inventors: Lakshmanan Valliappan, Moorthi Subramanivan
  • Patent number: 8807927
    Abstract: A flow control assembly is provided, including a member and a wall. The member has a surface, a flow diverting member and a rail member. The rail member is situated upstream of the flow diverting member. The flow diverting member and the rail member each project from the surface of the member. The flow diverting member has a distal end. The wall is disposed in relation to the member to create a clearance gap between the distal end of the flow diverting member and the wall. A fluid path is created between the member and the wall, and flows from an upstream section and through the clearance gap. A first chamber and a second chamber are defined by the wall and located upstream of the clearance gap.
    Type: Grant
    Filed: September 29, 2011
    Date of Patent: August 19, 2014
    Assignee: General Electric Company
    Inventors: Ramesh Kempanna Babu, Rohit Chouhan, Santhosh Kumar Vijayan
  • Patent number: 8800133
    Abstract: Gas turbine engine systems involving rotor bayonet coverplates and tools for installing such coverplates are provided. In this regard, a representative turbine assembly for a gas turbine engine includes: a turbine disk operative to mount a set of turbine blades; and a coverplate having an annular main body portion and a spaced annular arrangement of tabs extending radially inwardly from the main body portion with open-ended gaps being located between the tabs, the tabs being operative to secure an inner diameter of the coverplate to the turbine disk.
    Type: Grant
    Filed: July 9, 2012
    Date of Patent: August 12, 2014
    Assignee: United Technologies Corporation
    Inventors: Joseph T. Caprario, Daniel J. Griffin
  • Patent number: 8784045
    Abstract: A seal assembly including first and second components; a seal arranged between the first and second components to seal a secondary flow region from a primary flow region; and a second recess portion provided on a surface of the second component between the seal and the primary flow region, the second recess portion further being arranged to receive a first portion of a flow from the secondary flow region and being configured to promote a second flow feature within the second recess portion, wherein the second recess portion is set back from the surface of the second component such that a second portion of the flow from the secondary flow region bypasses the second recess portion.
    Type: Grant
    Filed: July 6, 2011
    Date of Patent: July 22, 2014
    Assignee: Rolls-Royce PLC
    Inventors: Tatjana Zoric, James D. Godwin
  • Patent number: 8784046
    Abstract: The turbine is provided with a blade (50) and a structure body (11) which rotates relatively with respect to the blade (50). A stepped part (52A) having a step surface (53A) is installed at one of the leading end of the blade (50) and the structure body (11) corresponding to the leading end thereof, while a seal fin (15A) which extends toward the stepped part (52A) to form a small space (H) is installed at the other of them. A cavity (C1) is formed between the blade (50) and the structure body (11) and also between the seal fin (15A) and the partition wall which faces thereto in the rotating shaft direction of the structure body (11) on the upstream side. When a distance of the cavity (C1) between the partition wall and the seal fin (15A) is given as a cavity width (W), and a distance between the seal fin (15A) and the end edge (55) of the stepped part (52A) in the rotating shaft direction on the upstream side is given as (L), at least one of the distances (L) satisfies the following formula (1). 0.7H?L?0.
    Type: Grant
    Filed: October 4, 2010
    Date of Patent: July 22, 2014
    Assignee: Mitsubishi Heavy Industries, Ltd.
    Inventors: Yoshihiro Kuwamura, Kazuyuki Matsumoto, Hiroharu Ooyama, Yoshinori Tanaka, Asaharu Matsuo
  • Publication number: 20140169954
    Abstract: A centrifugal turbomachine comprising a casing, a rotor assembly comprising at least one centrifugal impeller for a fluid flowing from an inlet side to an outlet side of the impeller, and an eye seal extending between an impeller eye of the centrifugal impeller and the casing for preventing the fluid from leaking between the casing and the centrifugal impeller, wherein the eye seal comprises at least a first portion toward the inlet side and a last portion toward the outlet side of the impeller, the last portion being smaller in diameter than the first portion.
    Type: Application
    Filed: July 20, 2012
    Publication date: June 19, 2014
    Inventors: Giuseppe Iurisci, Riccardo Brogelli
  • Publication number: 20140133971
    Abstract: A seal configuration includes a housing and a rotatable member rotationally mounted relative to the housing. The rotatable member has at least one portion defining an outer perimetrical face that is configured to contact the housing during operational conditions that cause a radial dimension of the at least one portion to increase. The at least one portion has opposing axial surfaces with each of the opposing axial surfaces being dimensionally axially nearer to the other of the opposing axial surfaces immediately radially inwardly of the outer perimetrical face than a furthest part of the outer perimetrical face.
    Type: Application
    Filed: November 14, 2012
    Publication date: May 15, 2014
    Applicant: GENERAL ELECTRIC COMPANY
    Inventors: David Richard Johns, Eric David Roush
  • Patent number: 8708646
    Abstract: A MCrAlY alloy, methods to produce a MCrAlY layer and a honeycomb seal are provided. The MCrAlY alloy includes chromium, aluminum, yttrium and iron and optionally titanium, hafnium or silicon. The honeycomb seal includes a substrate, honeycomb cells and a protective coating on side walls of the honeycomb cells or a diffusion area inside side walls of the honeycomb cells, the protective coating or the diffusion area including the MCrAlY alloy.
    Type: Grant
    Filed: January 23, 2009
    Date of Patent: April 29, 2014
    Assignee: Siemens Aktiengesellschaft
    Inventors: David Fairbourn, Paul Mathew Walker
  • Patent number: 8708639
    Abstract: The present application provides an axial flow turbine. The axial flow turbine may include a stator casing and a turbine bucket positioned about the stator casing. A tip shroud may be positioned on the turbine bucket. A shroud tail may be attached to the tip shroud at a downstream end of the tip shroud.
    Type: Grant
    Filed: October 11, 2010
    Date of Patent: April 29, 2014
    Assignee: The Coca-Cola Company
    Inventor: Moorthi Subramaniyan
  • Publication number: 20140064939
    Abstract: A metal sealing material used in a sealing device which can reduce a gap between a stator and a rotor of a turbine. The metal sealing material used in a sealing device for a stator and a rotor of a turbine includes a surface layer and a lower layer composed of a porous metal layer, wherein the porosity of the surface layer is smaller than the porosity of the lower layer; the porosity of the surface layer is 60 to 65% and the porosity of the lower layer is 67 to 75% or less; and the porous metal layer has a thickness of 0.3 to 3.0 mm and may include, as a main component, an MCrAlY alloy where M is either one of Ni and Co or both thereof, and h-BN as a solid lubricant.
    Type: Application
    Filed: August 28, 2013
    Publication date: March 6, 2014
    Applicant: HITACHI, LTD.
    Inventors: Yoshitaka KOJIMA, Hideyuki ARIKAWA, Akira MEBATA, Hiroyuki DOI, Hajime TORIYA, Kenjiro NARITA
  • Publication number: 20140064909
    Abstract: A labyrinth seal design, an actuation control clearance strategy, and a method of operating a turbomachine. The labyrinth seal design including a plurality of features configured to open and close radial clearances in response to relative axial movement between a stationary component and a rotating component. The actuation control clearance strategy and method of operating a turbomachine effective to achieve relative motion between a rotating component and a stationary component of the turbomachine using active elements. Axial displacement of the rotating component relative to the stationary component provides an adjustment in a radial clearance at one or more sealing locations between the rotating component and the stationary component to suit a given operating condition of the turbomachine.
    Type: Application
    Filed: August 28, 2012
    Publication date: March 6, 2014
    Applicant: GENERAL ELECTRIC COMPANY
    Inventors: Deepak Trivedi, Norman Arnold Turnquist, Xiaoqing Zheng, Murat Inalpolat
  • Patent number: 8662835
    Abstract: A turbine nozzle for a turbomachine, including inner and outer annular platforms connected together by vanes, the inner platform carrying annular elements of abradable material co-operating with annular wipers of a rotor of the turbomachine to form a labyrinth seal, these elements of abradable material being carried by annular sheet-metal sectors of substantially L-, S-, or C-shaped section that are fastened by brazing or welding at their outer peripheries to the inner platform and at their inner peripheries to the elements of abradable material.
    Type: Grant
    Filed: March 13, 2009
    Date of Patent: March 4, 2014
    Assignee: SNECMA
    Inventors: Thierry Fachat, Patrick Joseph Marie Girard, Jean-Luc Soupizon
  • Patent number: 8650753
    Abstract: A seal (48) between a compressor rotor blade (26) and compressor casing (28) comprises an abradable structure (59) on the compressor casing (28). The abradable structure (59) comprises a metallic foam (60) having pores (66, 68). The metallic foam (60) has a first a region (62) and a second region (64). The first region (62) of the metallic foam (60) is arranged adjacent to the compressor casing (28) and the second region (64) of the metallic foam (60) is spaced from the compressor casing (28) by the first region (62) of the metallic foam (60). The pores (68) of the second region (64) of the metallic foam (60) contain an abradable material (70) and the pores (66) of the first region (62) of the metallic foam (60) do not contain an abradable material.
    Type: Grant
    Filed: October 8, 2009
    Date of Patent: February 18, 2014
    Assignee: Rolls-Royce, PLC
    Inventors: Christopher Sellars, Glen Pattinson, John T Gent
  • Patent number: 8632309
    Abstract: A blade is disclosed for a gas turbine including an airfoil, which extends along a longitudinal axis from a blade root to a blade tip, and has a shroud segment at the blade tip. The shroud segment abuts with first and second edges against shroud segments of adjacent blades to form a ring-like shroud. The first and second edges are each provided with a respective side rail on the upper side of the shroud segment. Each of the side rails is subdivided into sections of different height and/or width.
    Type: Grant
    Filed: April 21, 2011
    Date of Patent: January 21, 2014
    Assignee: Alstom Technology Ltd
    Inventors: Igor Tsypkaykin, Ruben Valiente, Brian Kenneth Wardle, Beat Von Arx, Andre Saxer
  • Patent number: 8608424
    Abstract: A turbomachine includes a housing having an inner surface, a compressor, a turbine and a rotary member including a plurality of blade members configured as part of one of the compressor and the turbine. Each of the plurality of blade members includes a base portion and a tip portion. The turbomachine also includes a honeycomb seal member mounted to the inner surface of the housing adjacent the rotary member. The honeycomb seal member includes a contoured surface having formed therein a deformation zone. The deformation zone includes an inlet zone and an outlet zone. The inlet zone is spaced a first distance from the tip portion of each of the plurality of blade members and the outlet zone is spaced a second distance from the tip portion of each of the plurality of blade members. The second distance being substantially equal to or less than the first distance.
    Type: Grant
    Filed: October 9, 2009
    Date of Patent: December 17, 2013
    Assignee: General Electric Company
    Inventors: Sanjeev Kumar Jain, Joshy John, Sachin Kumar Rai, Rajnikumar Nandalal Suthar
  • Patent number: 8591181
    Abstract: A turbomachine seal assembly includes a plurality of sealing strips configured and disposed to inhibit a flow of fluid from passing through a channel defined by a first member and a second member. At least one of the plurality of sealing strips includes a paddle element that is configured and disposed to create a fluid recirculation zone at the channel. The fluid recirculation zone further inhibits the flow of fluid through the channel.
    Type: Grant
    Filed: October 18, 2010
    Date of Patent: November 26, 2013
    Assignee: General Electric Company
    Inventors: Ravi Shankar Venkata Kasibhotla, William Edward Adis, Venkata Siva Jagadeeswararao Anjuri, Anantha Padmanabhan Bhagavatheeswaran
  • Publication number: 20130272855
    Abstract: A turbine includes a blade, a structure installed at a tip section side of the blade via a gap and configured to relatively rotate with respect to the blade, a step section formed at the tip section of the blade, having at least one step surface, and protruding toward a portion opposite to the tip section of the structure, a seal fin formed at the portion opposite to the tip section of the structure, extending toward the step section, and configured to form a micro gap between the step section and the seal fin, and a cutout section formed at the step surface to be connected to an upper surface of the step section. The cutout section guides a separation vortex separated from a main stream of a fluid passing through the gap toward the seal fin on the upper surface of the step section.
    Type: Application
    Filed: December 22, 2011
    Publication date: October 17, 2013
    Inventors: Yoshihiro Kuwamura, Kazuyuki Matsumoto, Hiroharu Oyama, Yoshinori Tanaka, Asaharu Matsuo
  • Publication number: 20130236298
    Abstract: A sealing assembly for use with a rotary machine is described herein. The sealing assembly includes a stator shroud coupled to the casing. The stator shroud includes an inner surface that at least partially defines the cavity within the casing. At least one stator labyrinth tooth extends outwardly from the stator shroud inner surface towards a rotor assembly positioned within the casing. At least one protective member is coupled to the stator shroud upstream from the at least one stator labyrinth tooth to facilitate reducing a flow of combustion gas across the at least one stator labyrinth tooth.
    Type: Application
    Filed: March 9, 2012
    Publication date: September 12, 2013
    Inventor: Rohit Chouhan