Erodable Or Permanently Deformable Patents (Class 415/173.4)
  • Patent number: 10702964
    Abstract: A blade outer air seal for a gas turbine engine having a surface that is eccentric with respect to the engine rotation centerline, and a method for creating same, are disclosed. Also, a method for grinding a work piece having nominal curvature defined by a work piece curvature centerline is disclosed, comprising the steps of: a) determining a desired surface profile for the work piece; b) providing a rotating grinding surface having a grinding rotation centerline; c) offsetting the grinding rotation centerline from the work piece curvature centerline; and d) applying the rotating grinding surface to the work piece while rotating the rotating grinding surface about the grinding rotation centerline to create the desired surface profile.
    Type: Grant
    Filed: December 4, 2017
    Date of Patent: July 7, 2020
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Paul M. Lutjen, Patrick D. Couture
  • Patent number: 10690251
    Abstract: Labyrinth seal system includes stationary component and rotatable component, where one of the stationary and rotatable components includes teeth. The labyrinth seal system further includes abradable component coupled to surface of other of the stationary and rotatable components and disposed facing the teeth. The abradable component includes a plurality of honeycomb cells disposed adjacent to each other along axial direction and circumferential direction. Each honeycomb cell includes a plurality of radial sidewalls, where each radial sidewall includes first portion and second portion. The first portion is coupled to the surface and the second portion extends from the first portion towards clearance defined between the stationary and rotatable components. The second portion is bent relative to radial axis of the labyrinth seal system.
    Type: Grant
    Filed: September 6, 2017
    Date of Patent: June 23, 2020
    Assignee: General Electric Company
    Inventors: Krishnendu Saha, Deoras Prabhudharwadkar, Ashok Gopinath
  • Patent number: 10662949
    Abstract: A radial compressor employs a compressor wheel having an inducer. An inlet air passage has a first region and a second region separated from the first region by a divider wall. The divider wall extends from an inlet plane of the inducer and connects the first region to a first air filter and said second region to a second air filter.
    Type: Grant
    Filed: June 22, 2017
    Date of Patent: May 26, 2020
    Inventor: Steven Don Arnold
  • Patent number: 10563537
    Abstract: An apparatus includes first, second, and third layers. The first layer includes a plurality of flanges. The second layer includes a deformable membrane. The second layer is connected to the first layer along a first major surface of the deformable membrane. The third layer is connected to the second layer along a second major surface of the deformable membrane opposite the first major surface. The third layer includes a first series of internal structures.
    Type: Grant
    Filed: February 5, 2016
    Date of Patent: February 18, 2020
    Assignee: United Technologies Corporation
    Inventors: Wendell V. Twelves, Jr., Evan Butcher, Lexia Kironn, Joe Ott, Gary D. Roberge
  • Patent number: 10527061
    Abstract: A centrifugal compressor includes a housing that accommodates an impeller. The housing includes a motor housing, a speed-increasing gear housing, and a compressor housing. The compressor housing has a suction port through which air is drawn in. The compressor housing includes a cylindrical main body, a cylindrical boss, and a fitting portion having a shape of a truncated cone. The cylindrical boss projects from the main body. The boss includes an injection port for spraying water that is generated through power generation by a fuel cell to air flowing through the suction port toward an impeller chamber.
    Type: Grant
    Filed: March 17, 2017
    Date of Patent: January 7, 2020
    Assignee: KABUSHIKI KAISHA TOYOTA JIDOSHOKKI
    Inventors: Ryosuke Fukuyama, Shogo Ito
  • Patent number: 10465716
    Abstract: A gas turbine engine shroud for surrounding one of a rotor and a stator having a plurality of radially extending airfoils is provided. The shroud includes an annular body defining an axial and a radial direction. The body has a radially inner surface and a plurality of indentations is annularly defined therein. Each of the plurality of indentations has a depth of an order of magnitude of a clearance between the one of the rotor and the stator and the inner surface. The plurality of indentations is defined in a region of the inner face defined axially between projections of leading and trailing edges of the airfoils onto the inner surface of the annular body.
    Type: Grant
    Filed: November 14, 2014
    Date of Patent: November 5, 2019
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Huu Duc Vo, Mert Cevik, Engin Erler
  • Patent number: 10465548
    Abstract: A method for implementing an abradable coating comprising: a pattern-forming step in which, using a slurry containing ceramic particles and solvent, a slurry pattern is formed on the surface of a thermal barrier coating layer; and a firing step in which the slurry pattern formed on the surface of the thermal barrier coating layer is fired to form an abradable coating layer. A ceramic material included in the thermal barrier coating layer and ceramic particles included in the abradable coating layer are of the same type.
    Type: Grant
    Filed: January 5, 2017
    Date of Patent: November 5, 2019
    Assignee: MITSUBISHI HEAVY INDUSTRIES AERO ENGINES, LTD.
    Inventors: Takayuki Kurimura, Mineaki Matsumoto, Tadayuki Hanada, Azusa Tamugi
  • Patent number: 10458256
    Abstract: A thermal barrier system includes a protective coating on a substrate, and a ceramic feature layer attached to the protective coating via an adhesive spray coat.
    Type: Grant
    Filed: October 27, 2015
    Date of Patent: October 29, 2019
    Assignee: United Technologies Corporation
    Inventors: Christopher W Strock, Paul M Lutjen
  • Patent number: 10408078
    Abstract: One aspect of the disclosure involves a nib material comprising a polymeric matrix and carbon nanotubes in the matrix. In one or more embodiments of any of the foregoing embodiments, the matrix comprises a silicone. In one or more embodiments of any of the foregoing embodiments, the rub material is at least 1.0 mm thick. In one or more embodiments of any of the foregoing embodiments, the silicone is selected from the group consisting of dimethyl- and fluoro-silicone rubbers and their copolymers. In one or more embodiments of any of the foregoing embodiments, the carbon nanotubes at least locally have a concentration of 1-20% by weight.
    Type: Grant
    Filed: January 29, 2013
    Date of Patent: September 10, 2019
    Assignee: United Technologies Corporation
    Inventors: Christopher W. Strock, Changsheng Guo
  • Patent number: 10400786
    Abstract: A rotor for a turbomachine is provided which includes a hub; and a plurality of blades extending radially from the hub, the plurality of blades comprising a first subset of blades having first tips and an abrasive coating on the first tips, and a second subset of blades having second tips with no abrasive coating on the second tips, wherein a radius (R2) of the first subset of blades, including thickness of the abrasive coating, is greater than a radius (R1) of the second subset of blades, and wherein a base radius (R) of the first subset of blades, not including thickness of the abrasive coating, is less than the radius (R1) of the second subset of blades.
    Type: Grant
    Filed: November 7, 2016
    Date of Patent: September 3, 2019
    Assignee: United Technologies Corporation
    Inventors: Agnieszka M. Wusatowska-Sarnek, Sergei F. Burlatsky, David Ulrich Furrer, J. Michael McQuade
  • Patent number: 10378450
    Abstract: A method of manufacturing a gas turbine engine air seal comprising forming at least one MAX phase particle. The method includes coating the at least one MAX phase particle with a metallic shell. The method includes applying the at least one MAX phase metallic coated particle to a surface of a substrate of the air seal to form an abradable layer of a MAXMET composite abradable material from the at least on MAX phase metallic coated particle.
    Type: Grant
    Filed: May 27, 2015
    Date of Patent: August 13, 2019
    Assignee: United Technologies Corporation
    Inventors: Shahram Amini, Christopher W. Strock, Weina Li
  • Patent number: 10370998
    Abstract: A segmented turbine shroud for radially encasing a turbine in a gas turbine engine comprises a carrier comprising a flange; a ceramic matrix composite (CMC) seal segment comprising a portion defining a pin-receiving bore; an elongated pin extending through the pin-receiving bore; a bushing surrounding the elongated pin within the bore; and a flexible mounting member, the flexible mounting member being connected to the bushing and the carrier flange to thereby flexibly mount the CMC seal segment to the carrier.
    Type: Grant
    Filed: May 26, 2015
    Date of Patent: August 6, 2019
    Assignees: ROLLS-ROYCE CORPORATION, ROLLS-ROYCE NORTH AMERICAN TECHNOLOGIES INC., ROLLS-ROYCE HIGH TEMPERATURE COMPOSITES INC.
    Inventors: Daniel Kent Vetters, Todd Engel, Matt Brandt
  • Patent number: 10309243
    Abstract: A blade outer air seal for a turbomachine includes a base portion configured to attach to a turbomachine housing, a thermal coating disposed on the base portion, and at least one groove defined in an external surface of the thermal coating. The groove can be machined. A method of manufacturing a blade outer air seal includes disposing a thermal coating on a base portion, and machining at least one groove into the thermal coating. The method can also include using an automated force sensing and vision sensing equipped robotic system.
    Type: Grant
    Filed: May 11, 2015
    Date of Patent: June 4, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Michael G McCaffrey, Alan C. Barron
  • Patent number: 10309238
    Abstract: A gas turbine engine component includes a passage and a geometrically segmented coating section adjacent the passage. The geometrically segmented coating section includes a wall that has a first side bordering the passage and a second side opposite the first side. The second side includes an array of cells, and there is a coating disposed over the array of cells. The coating defines an exterior side. A cooling passage extends through the wall and the coating. The cooling passage fluidly connects the passage and the exterior side.
    Type: Grant
    Filed: November 17, 2016
    Date of Patent: June 4, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventor: Tracy A. Propheter-Hinckley
  • Patent number: 10309226
    Abstract: An airfoil includes an airfoil section that defines an airfoil profile. The airfoil section includes a panel that forms a portion of the airfoil profile and a core structure to which the panel is secured.
    Type: Grant
    Filed: November 17, 2016
    Date of Patent: June 4, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventor: Raymond Surace
  • Patent number: 10287646
    Abstract: Provided is a porous metal body having superior corrosion resistance to conventional metal porous bodies composed of nickel-tin binary alloys and conventional metal porous bodies composed of nickel-chromium binary alloys. The porous metal body has a three-dimensional network skeleton and contains at least nickel, tin, and chromium. The concentration of chromium contained in the porous metal body is highest at the surface of the skeleton of the porous metal body and decreases toward the inner side of the skeleton. In one embodiment, the chromium concentration at the surface of the skeleton of the porous metal body is more preferably 3% by mass or more and 70% by mass or less.
    Type: Grant
    Filed: April 9, 2014
    Date of Patent: May 14, 2019
    Assignees: SUMITOMO ELECTRIC INDUSTRIES, LTD., SUMITOMO ELECTRIC TOYAMA CO., LTD.
    Inventors: Kazuki Okuno, Masatoshi Majima, Kengo Tsukamoto, Hitoshi Tsuchida, Hidetoshi Saito
  • Patent number: 10227876
    Abstract: A blade for a gas turbine engine comprises an airfoil having a pressure side and a suction side, with a root and a tip wall. The pressure side and suction side extend beyond the tip wall to define a tip channel, defining a plurality of internal and external corners. The corners comprise fillets to define a thickness being greater than the thickness for the pressure, suction, or tip walls. A film hole can extend through the fillet, such that the length of the film hole at the fillet can be increased to define an increased length-to-diameter ratio for the film hole to improve film cooling through the film hole.
    Type: Grant
    Filed: December 7, 2015
    Date of Patent: March 12, 2019
    Assignee: General Electric Company
    Inventors: Jared Peter Buhler, Ronald Scott Bunker, Victor Hugo Silva Correia, Brian Kenneth Corsetti
  • Patent number: 10197067
    Abstract: According to an aspect of an exemplary embodiment, there is provided a rotation body of a rotary machine, the rotation body comprising: an impeller comprising a blade; and a shroud that is integrally formed with the impeller and has a cladding stack structure in which a plurality of laser cladding layers are stacked.
    Type: Grant
    Filed: February 13, 2013
    Date of Patent: February 5, 2019
    Assignee: HANWHA AEROSPACE CO., LTD.
    Inventor: Sung-Chul Ahn
  • Patent number: 10190488
    Abstract: A method for producing a variable turbine geometry of a charging device may include inserting at least two guide blades into a blade mounting ring. The method may then include jointly machining at least two of the guide blades, in the mounted state, on respective end side of the at least two guide blades facing away from the blade mounting ring in order to produce a final shape of the end sides.
    Type: Grant
    Filed: January 22, 2016
    Date of Patent: January 29, 2019
    Assignee: Bosch Mahle Turbo Systems GmbH & Co. KG
    Inventors: Dirk Naunheim, Daren Bolbolan
  • Patent number: 10183312
    Abstract: An abrasive coating for a metal airfoil tip in a gas turbine engine may include a plurality of grit particles coated with a braze alloy material and configured for attachment to the airfoil tip. The braze alloy may be a nickel base, cobalt base or iron base braze alloy or mixtures thereof, or a titanium base braze alloy.
    Type: Grant
    Filed: May 7, 2015
    Date of Patent: January 22, 2019
    Assignee: United Technologies Corporation
    Inventors: Christopher W. Strock, Changsheng Guo
  • Patent number: 10053993
    Abstract: A shrouded turbine airfoil (10) with a leakage flow conditioner (12) configured to direct leakage flow to be aligned with main hot gas flow is disclosed. The leakage flow conditioner (12) may be positioned on a radially outer surface (18) of an outer shroud base (20) of the outer shroud (22) on a tip (24) of an airfoil (10). The leakage flow conditioner (12) may include a radially outer surface (28) that is positioned further radially inward than the radially outer surface (18) of the outer shroud base (20) creating a radially outward extending wall surface (30) that serves to redirect leakage flow. In at least one embodiment, the radially outward extending wall surface (30) may be aligned with a pressure side (38) of the shrouded turbine airfoil (10) to increase the efficiency of a turbine engine by redirecting leakage flow to be aligned with main hot gas flow to reduce aerodynamic loss upon re-introduction to the main gas flow.
    Type: Grant
    Filed: March 17, 2015
    Date of Patent: August 21, 2018
    Assignee: SIEMENS ENERGY, INC.
    Inventors: Kok-Mun Tham, Ching-Pang Lee, Li Shing Wong, Andrew S. Lohaus, Farzad Taremi
  • Patent number: 10024193
    Abstract: The present disclosure is directed to a component for a gas turbine. The component includes a component wall having a radially inner surface, a radially outer surface, a first circumferential surface, and a second circumferential surface. A first boss extends radially outwardly from the radially outer surface, includes a first circumferentially outer surface, and defines a first aperture extending axially therethrough. A second boss extends radially outwardly from the radially outer surface and is circumferentially spaced apart from the first boss. The second boss includes a second circumferentially outer surface and defines a second aperture extending axially therethrough. The first circumferentially outer surface of the first boss and the second circumferentially outer surface of the second boss form a pair of angles with respect to the radially inner surface.
    Type: Grant
    Filed: November 19, 2015
    Date of Patent: July 17, 2018
    Assignee: General Electric Company
    Inventor: Jason David Shapiro
  • Patent number: 10024191
    Abstract: A containment system for a gas turbine engine includes a fan track assembly for use with a containment case. The fan track assembly includes a body of collapsible material that is positioned within a cavity of the fan case, and voids are provided for providing space in the event of a catastrophic blade failure. Various configurations of the fan track liner assembly are provided along with various mounting methodologies for securing the track liner assembly to the fan case of a gas turbine engine.
    Type: Grant
    Filed: September 5, 2013
    Date of Patent: July 17, 2018
    Assignee: ROLLS-ROYCE CORPORATION
    Inventors: Trevor John Totten, Jonathan Michael Rivers, Eric William Engebretsen, Matthew Joseph Kappes
  • Patent number: 9951642
    Abstract: An abradable material includes a matrix material defining pockets of fluid. The abradable material also includes an outer surface configured to be coupled to an interior surface of a fan case such that in response to the outer surface being coupled to the fan case, the abradable material is positioned circumferentially about an axis The abradable material also includes an inner surface defining a circumferential ridge and a circumferential groove.
    Type: Grant
    Filed: May 8, 2015
    Date of Patent: April 24, 2018
    Assignee: United Technologies Corporation
    Inventor: William Bogue
  • Patent number: 9932904
    Abstract: An exhaust gas turbocharger may include a compressor housing and a turbine housing. The turbine housing may be connected to the compressor housing via a plurality of spacer pins composed of a heat-insulating material. The plurality of spacer pins may respectively include a head and at least one axial pin.
    Type: Grant
    Filed: March 31, 2015
    Date of Patent: April 3, 2018
    Assignee: Bosch MahleTurbo Systems GmbH & Co. KG
    Inventor: Michal Klusacek
  • Patent number: 9920646
    Abstract: Turbine and compressor casing/housing abradable component embodiments for turbine engines, have abradable surfaces with asymmetric forward and aft ridge surface area density. The forward ridges have greater surface area density than the aft ridges to compensate for greater ridge erosion in the forward zone during engine operation and reduce blade tip wear in the aft zone. Some abradable component embodiments increase forward zone ridge surface area density by incorporating wider ridges than those in the aft zone.
    Type: Grant
    Filed: February 18, 2015
    Date of Patent: March 20, 2018
    Assignee: Siemens Aktiengesellschaft
    Inventors: Ching-Pang Lee, Kok-Mun Tham, Gm Salam Azad, Zhihong Gao, Erik Johnson, Eric Schroeder, Nicholas F. Martin, Jr.
  • Patent number: 9909428
    Abstract: Turbine buckets include a pressure side, a suction side opposite the pressure side, and a bucket squealer tip attached to the pressure side and the suction side. The bucket squealer tip includes a plurality of high hot hardness shroud-cutting deposits deposited on its exterior surface that have a hardness of at least about 1100 kg mm?2 and a melting temperature of at least about 1500° C.
    Type: Grant
    Filed: November 26, 2013
    Date of Patent: March 6, 2018
    Assignee: General Electric Company
    Inventors: Srikanth Chandrudu Kottilingam, Surinder Singh Pabla, Brian Lee Tollison
  • Patent number: 9903210
    Abstract: A turbine blade tip shroud (22C, 22D) with a seal rail (32C, 32D) oriented in a circumferential direction of rotation (29) relative to a turbine axis, and extending radially outward from the tip relative to the turbine axis. A first tooth (48, 68) and a second tooth (50, 70) form respective downstream and upstream lateral departures or bumps on the seal rail. Each tooth has a sharp top leading edge (48, 50, 68, 70) and a smoothly curved side surface (49, 51, 69, 71). A back portion (56, 76) of the seal rail may span linearly from a lateral peak (66, 78) of the second tooth to a back end (62) of the seal rail that is centered on an extended centerline (60) of a front portion (54, 74) of the seal rail. The teeth may be disposed proximate or over a stacking axis (52) of the blade.
    Type: Grant
    Filed: May 20, 2014
    Date of Patent: February 27, 2018
    Assignee: SIEMENS ENERGY, INC.
    Inventors: Charles M. Evans, Andrew R. Narcus, John Pula
  • Patent number: 9833869
    Abstract: A blade outer air seal for a gas turbine engine having a surface that is eccentric with respect to the engine rotation centerline, and a method for creating same, are disclosed. Also, a method for grinding a work piece having nominal curvature defined by a work piece curvature centerline is disclosed, comprising the steps of: a) determining a desired surface profile for the work piece; b) providing a rotating grinding surface having a grinding rotation centerline; c) offsetting the grinding rotation centerline from the work piece curvature centerline; and d) applying the rotating grinding surface to the work piece while rotating the rotating grinding surface about the grinding rotation centerline to create the desired surface profile.
    Type: Grant
    Filed: February 10, 2014
    Date of Patent: December 5, 2017
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Paul M. Lutjen, Patrick D. Couture
  • Patent number: 9758895
    Abstract: An Al2O3-coated co-deposit including an Ni-based alloy substrate, an exterior layer present on a surface of the substrate, wherein the exterior layer comprises NiCrAlY or NiCoCrAlY particles with a diameter of 0.5-50 ?m, Ni nanoparticles with a diameter of 0.1-10 nm in the form of a matrix, and Al2O3 particles that are present on the exterior surface of the exterior layer. A method for manufacturing the Al2O3-coated co-deposit whereby a substrate is immersed into a solution comprising at least one dissolved nickel salt, NiCrAlY or NiCoCrAlY particles, and Al particles in an electrochemical cell, DC current is pulsed into the electrochemical cell to electrodeposit Al, Ni, and NiCrAlY or NiCoCrAlY particles onto the substrate to form a deposited layer, and the substrate comprising the deposited layer is calcined to oxidize the Al particles and form the Al2O3-coated co-deposit.
    Type: Grant
    Filed: September 3, 2015
    Date of Patent: September 12, 2017
    Assignee: King Fahd University of Petroleum and Minerals
    Inventors: Anwar Ul-Hamid, Hatim Dafalla Mohamed Dafalla
  • Patent number: 9631506
    Abstract: Turbine and compressor casing abradable component embodiments for turbine engines, with composite, non-inflected, bi-angle, “hockey stick” like pattern abradable surface ridges and grooves. Some embodiments include distinct forward upstream and aft downstream composite multi orientation groove and vertically projecting ridges planform patterns, to reduce, redirect and/or block blade tip airflow leakage downstream into the grooves rather than from turbine blade airfoil high to low pressure sides. In some embodiments the grooves are split or divided into multiple sections to interrupt flow traveling inside the groove and cause a local pressurization that reduces tip leakage flow. Some ridge or rib embodiments also have first lower and second upper wear zones. The lower zone optimizes engine airflow characteristics while the upper zone is optimized to minimize blade tip gap and wear by being more easily abradable than the lower zone.
    Type: Grant
    Filed: February 18, 2015
    Date of Patent: April 25, 2017
    Assignee: Siemens Aktiengesellschaft
    Inventors: Ching-Pang Lee, Erik Johnson, Steven Koester, Jr.
  • Patent number: 9579714
    Abstract: A mold assembly for use in forming a component having an internal passage defined therein is provided. The component is formed from a component material. The mold assembly includes a mold that defines a mold cavity therein. The mold assembly also includes a lattice structure selectively positioned at least partially within the mold cavity. The lattice structure is formed from a first material that is at least partially absorbable by the component material in a molten state. A channel is defined through the lattice structure, and a core is positioned in the channel such that at least a portion of the core extends within the mold cavity and defines the internal passage when the component is formed in the mold assembly.
    Type: Grant
    Filed: December 17, 2015
    Date of Patent: February 28, 2017
    Assignee: General Electric Company
    Inventor: Stephen Francis Rutkowski
  • Patent number: 9464530
    Abstract: The present application and the resultant patent provide a turbine bucket for a gas turbine engine. The turbine bucket may include an airfoil, a tip shroud positioned radially outward from the airfoil, and a seal rail positioned radially outward from the tip shroud and extending in a generally tangential direction from a first end to a second end of the tip shroud. The seal rail may include a maximum axial thickness at a location positioned between the first end and the second end and offset from the airfoil in the generally tangential direction. The present application and the resultant patent further provide a gas turbine engine and a method for balancing a tip shroud of a turbine bucket of a gas turbine engine.
    Type: Grant
    Filed: February 20, 2014
    Date of Patent: October 11, 2016
    Assignee: General Electric Company
    Inventors: Spencer Aaron Kareff, Matthew Robert Piersall, Danielle Werner
  • Patent number: 9447503
    Abstract: A composite article includes a substrate and a thermal barrier secured to the substrate. The thermal barrier includes a plurality of closed pores within a ceramic matrix. For example, the closed pores comprise 20 vol % to 80 vol % of the thermal barrier.
    Type: Grant
    Filed: May 30, 2007
    Date of Patent: September 20, 2016
    Assignee: United Technologies Corporation
    Inventors: Susan M. Tholen, Christopher W. Strock
  • Patent number: 9297269
    Abstract: A gas turbine component (20) with a layer of ceramic material (22) defining a wear surface (21), in which an array of cross-shaped depressions (26A, 26B) formed in the wear surface (21) define a continuous labyrinth of orthogonal walls (28, 30) of the ceramic material, and reduce the area of the wear surface (21) by about 50%. Within a representative area (36) of the wear surface (21), the depressions (26A, 26B) provide a ratio of a lineal sum of depression perimeters (27) divided by the representative area (36) of the wear surface of least 0.9 per unit of measurement for improved abradability characteristics of the wear surface (21).
    Type: Grant
    Filed: May 7, 2007
    Date of Patent: March 29, 2016
    Assignee: Siemens Energy, Inc.
    Inventors: Jay A. Morrison, Jay E. Lane, Gary B. Merrill
  • Patent number: 9291065
    Abstract: A turbine including a plurality of stages, each stage including a rotatable disk and blades carried thereby. An annular gap defined between a pair of adjacent rotatable disks. A sealing band is located in opposing sealing band receiving slots formed in the adjacent disks to seal the annular gap, the sealing band including band engagement structure. A disk engagement structure is defined in the pair of adjacent rotatable disks. The disk engagement structure extends axially into the pair of adjacent rotatable disks and circumferentially aligns with the band engagement structure. A clip member is positioned in engagement with the sealing band through the band engagement structure and in engagement with the pair of adjacent rotatable disks through the disk engagement structure. The clip member restricts movement of the sealing band in only a circumferential direction of the slots.
    Type: Grant
    Filed: March 8, 2013
    Date of Patent: March 22, 2016
    Assignee: SIEMENS AKTIENGESELLSCHAFT
    Inventors: Christopher J Muller, David J Mitchell, Michael J Olejarski
  • Patent number: 9249680
    Abstract: Turbine and compressor casing abradable component embodiments for turbine engines, with composite grooves and vertically projecting asymmetric non-parallel walls or trapezoidal cross section ridges that reduce, redirect and/or block blade tip airflow leakage downstream into the grooves rather than from turbine blade airfoil high to low pressure sides. In some embodiments at least one angularly oriented first groove formed in the ridge plateau is adapted for angular orientation upstream a turbine blade rotation direction to resist blade tip airflow leakage and the ridges are separated by second grooves that are skewed relative to the respective ridge plateaus and the substrate that are also adapted for orientation upstream the turbine blade rotation direction to resist blade tip airflow leakage.
    Type: Grant
    Filed: February 25, 2014
    Date of Patent: February 2, 2016
    Assignee: SIEMENS ENERGY, INC.
    Inventors: Ching-Pang Lee, Gm Salam Azad, Zhihong Gao, Neil Hitchman, Nicholas F. Martin, Jr., David G. Sansom, Ramesh Subramanian
  • Patent number: 9151174
    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: Grant
    Filed: March 9, 2012
    Date of Patent: October 6, 2015
    Assignee: General Electric Company
    Inventor: Rohit Chouhan
  • Patent number: 9115596
    Abstract: A blade outer air seal (BOAS) for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a seal body having a radially inner face and a radially outer face that axially extend between a leading edge portion and a trailing edge portion. At least one of the leading edge portion and the trailing edge portion includes a solid wall and a perforated wall. At least a portion of the perforated wall is spaced from the solid wall such that a passage extends between the solid wall and the perforated wall.
    Type: Grant
    Filed: August 7, 2012
    Date of Patent: August 25, 2015
    Assignee: United Technologies Corporation
    Inventor: Brian Ellis Clouse
  • Publication number: 20150139787
    Abstract: An annular turbine engine stator portion including a structural support provided in succession with a bonding underlayer and with an abradable coating formed by a resin filled with microbeads, the bonding underlayer for fastening the abradable coating to the structural support being formed by fiber reinforcement made of long fibers having a peripheral portion of the reinforcement that is secured to the structural support and having a central portion thereof that is impregnated with the resin filled with microbeads while the abradable coating is being fastened to the structural support.
    Type: Application
    Filed: May 30, 2013
    Publication date: May 21, 2015
    Applicant: SNECMA
    Inventors: Philippe, Charles Alain Le Biez, Nicolas Cornacchia, Lionel Marcin, Pierre Marie Montfort
  • Publication number: 20150118031
    Abstract: The various embodiments of the present invention provide a method for installing a tip shroud on a turbine disk in a steam turbine. A tip shroud in the form of a ring is installed on the outer periphery of the turbine disk to prevent a leakage of the driving fluid. The method comprises the steps of mounting turbine disk on to a rotor shaft, tapering the outer diameter of the turbine disk and the inner diameter of the tip shroud, aligning and mounting the tapered surface of the turbine disk with the tapered surface of the tip shroud and fastening the tip shroud on the turbine disk with the help of fasteners. The bolted tip shroud is finally machined to reduce the outer peripheral diameter to appropriate dimensions.
    Type: Application
    Filed: October 14, 2014
    Publication date: April 30, 2015
    Inventor: KRISHNA KUMAR BINDINGNAVALE RANGA
  • Publication number: 20150093237
    Abstract: A ceramic matrix composite component, turbine system and fabrication process are disclosed. The ceramic matrix composite (CMC) component includes a CMC material, an environmental barrier coating (EBC) on the CMC material, and a hard wear coating applied over the EBC. The turbine system includes a rotatable CMC component having a hard wear coating, and a stationary turbine component, the stationary turbine component having an abradable coating arranged and disposed to be cut by the silicon carbide material. The fabrication process includes positioning the rotatable CMC a pre-determined distance from the stationary turbine component and rotating the rotatable CMC component. The hard wear coating on the rotatable CMC component cuts the abradable coating on the stationary turbine component.
    Type: Application
    Filed: September 30, 2013
    Publication date: April 2, 2015
    Applicant: GENERAL ELECTRIC COMPANY
    Inventor: John McConnell DELVAUX
  • Patent number: 8967972
    Abstract: A turbine blade is provided and includes a tip end carrying a shroud and at least one fin, which extends radially away from the shroud. The fin includes a first sidewall and a second sidewall, which are spaced apart, arranged parallel to each other, and are connected to the shroud, and a cutting edge, which is connected to the first and second sidewalls. The cutting edge thereby creates a hollow space between the sidewalls, the shroud, and the cutting edge, and further extends radially away from the first and second sidewalls. Also provided is a method of manufacturing the blade by casting the blade as single piece with the hollow fin or by forging the blade; and machining the fin to create the first and second sidewalls and cutting edge thereby opening the hollow space between said sidewalls and the cutting edge.
    Type: Grant
    Filed: November 2, 2012
    Date of Patent: March 3, 2015
    Assignee: ALSTOM Technology Ltd.
    Inventors: Herbert Brandl, Igor Tsypkakyin, Philipp Indlekofer
  • Publication number: 20150044035
    Abstract: An abradable coating for a gas turbine engine includes a bond coat, an intermediate layer, and a porous layer. The bond coat includes a metal coating and a thickness from 0.152 millimeters to 0.229 millimeters. The intermediate layer includes a ceramic material and a thickness from 0.051 millimeters to 0.381 millimeters. The porous layer includes a porous ceramic material. The porous layer also includes a porosity greater than thirty-five percent of a volume of the porous layer. The porous layer further includes a thickness from 0.127 millimeters to 1.524 millimeters.
    Type: Application
    Filed: August 8, 2013
    Publication date: February 12, 2015
    Applicant: SOLAR TURBINES INCORPORATED
    Inventors: Brent Allen Cottom, Michael Andrew Coe
  • Patent number: 8951008
    Abstract: The invention relates to a compressor blade of a compressor which, along a main axis, comprises a blade base, a platform area and an adjacent blade profile having a profile tip. The blade profile is configured by a convex wall at the suction end and a concave wall at the pressure end opposite the wall at the suction end. These surfaces extend, with respect to a flow medium, from a leading edge to a trailing edge, a profile center line extending in the center between the two. A front face is arranged on the profile tip at an angle to the main axis, a sealing lip at least partially extending from the leading edge to the trailing edge and the blade profile including the sealing lip having a blade profile height extending in the direction of the main axis. In order to allow for an inexpensive compressor blade having improved aerodynamic properties and a modified sealing lip while having the same sealing properties, the height of the sealing lip is less than 2 percent of the height of the blade profile.
    Type: Grant
    Filed: June 20, 2005
    Date of Patent: February 10, 2015
    Assignee: Siemens Aktiengesellschaft
    Inventors: Christian Cornelius, Bernhard Küsters, Stephan Mais, Andreas Peters, Achim Schirrmacher, Lutz Stephan, Bernd van den Toorn
  • Patent number: 8950069
    Abstract: A low leakage, integral fixed vane system for a gas turbine engine compression system which can accommodate the latest 3-D aerodynamic airfoil geometries and provide endwall ovalization control. A unitized construction wherein the vanes are integral with the case wall in the compression system.
    Type: Grant
    Filed: December 21, 2007
    Date of Patent: February 10, 2015
    Assignee: Rolls-Royce North American Technologies, Inc.
    Inventor: Robert A. Ress, Jr.
  • Patent number: 8939712
    Abstract: The invention relates to a housing for covering the ends of a row of rotor blades of an axial turbomachine compressor, the housing being provided with a sealing device between the blade tips and the housing. It comprises a shell segmented along its circumference, each segment being fixed to the housing by a series of elastomeric elements in a recess in the shape of a channel cut into the inner surface of the housing. In this way, in the event of misalignment of the rotor relative to the stator, the rotor blades coming into contact with sections of the shell will be able to move to compensate for this misalignment while reducing the frictional forces generated by contact between the blades and the shell. In the event of alignment being re-established the segments of the shell will be able to resume their initial position because of the elastic behavior of the elements.
    Type: Grant
    Filed: February 29, 2012
    Date of Patent: January 27, 2015
    Assignee: Techspace Aero S.A.
    Inventor: Jean-Francois Cortequisse
  • Patent number: 8939706
    Abstract: Turbine and compressor casing abradable component embodiments for turbine engines, with composite grooves and vertically projecting rows of ridges in planform patterns, establishing upper and lower wear zones. The lower wear zone reduces, redirects and/or blocks blade tip downstream airflow leakage, while the upper wear zone is optimized to minimize blade tip gap and wear by being more easily abradable than the lower zone. An elongated first ridge in the lower wear zone terminates in a continuous surface plateau. A plurality of second ridges or nibs, separated by grooves, project from the plateau, forming the upper wear zone. Each of the second ridges has a planform cross section smaller than the plateau planform cross section and a height smaller than the first ridge height. Some embodiments of the second ridges have spacing, planform cross sections, heights and separating groove dimensions selected for shearing when contacted by turbine blade tips.
    Type: Grant
    Filed: February 25, 2014
    Date of Patent: January 27, 2015
    Assignee: Siemens Energy, Inc.
    Inventors: Ching-Pang Lee, Kok-Mun Tham, Gm Salam Azad, Zhihong Gao, Neil Hitchman, David G. Sansom, Barrry L. Allmon, Jonathan E. Shipper, Jr., Cora Schillig, Gary B. Merrill, Dimitrios Zois, Ramesh Subramanian
  • Patent number: 8939716
    Abstract: Turbine and compressor casing abradable component embodiments for turbine engines, with nested loop pattern abradable surface ridges and grooves. The nested loops comprise nested fully closed loops or a spiraling maze pattern loop. Some embodiments include distinct forward upstream and aft downstream composite multi orientation groove and vertically projecting ridges planform patterns, to reduce, redirect and/or block blade tip airflow leakage downstream into the grooves rather than from turbine blade airfoil high to low pressure sides. Ridge or rib embodiments have first lower and second upper wear zones. The lower zone optimizes engine airflow characteristics while the upper zone is optimized to minimize blade tip gap and wear by being more easily abradable than the lower zone.
    Type: Grant
    Filed: February 25, 2014
    Date of Patent: January 27, 2015
    Assignee: Siemens Aktiengesellschaft
    Inventors: Ching-Pang Lee, Kok-Mun Tham, Vincent P. Laurello, Gm Salam Azad, Nicholas F. Martin, Jr.
  • Patent number: 8939707
    Abstract: Turbine and compressor casing abradable component embodiments for turbine engines, with composite grooves and vertically projecting rows of stepped first ridges in planform patterns, to reduce, redirect and/or block blade tip airflow leakage downstream into the grooves rather than from turbine blade airfoil high to low pressure sides. Each stepped first ridge has a first portion proximal the substrate surface with a pair of first opposed lateral walls terminating in a plateau, and a second portion terminating in a ridge tip. These ridge or rib embodiments have first lower and second upper wear zones. The lower zone, which at and below first portion height, optimizes engine airflow characteristics, while the upper zone, between the plateau and the second portion ridge is optimized to minimize blade tip gap and wear by being more easily abradable than the lower zone.
    Type: Grant
    Filed: February 25, 2014
    Date of Patent: January 27, 2015
    Assignee: Siemens Energy, Inc.
    Inventors: Ching-Pang Lee, Kok-Mun Tham, Gm Salam Azad, Zhihong Gao, Neil Hitchman, David G. Sansom, Barrry L. Allmon